Dynamic antenna platform offset calibration

ABSTRACT

Systems and methods are described for supporting dynamic antenna platform offset calibration for an antenna system mounted to a mobile vehicle. In particular, dynamic antenna platform offset calibration can be performed while communicating user data associated with the mobile vehicle (e.g., based at least in part on alignment calibration procedures including measurements of user data signals), with an antenna platform offset being updated when alignment calibration procedures have been performed at suitably separated spatial conditions. Accordingly, antenna platform offset calibration may be performed throughout the operation of the mobile vehicle without requiring that the vehicle be proactively aligned in a particular orientation for a dedicated calibration routine prior to using the antenna for communicating user data during normal operation of the mobile vehicle.

CROSS REFERENCES

The present Application for patent is a Continuation of U.S. patentapplication Ser. No. 16/229,470 by MERRELL, entitled “Dynamic AntennaPlatform Offset Calibration” filed Dec. 21, 2018, which is aContinuation of U.S. patent application Ser. No. 15/642,808 by MERRELL,entitled “Dynamic Antenna Platform Offset Calibration,” filed Jul. 6,2017, assigned to the assignee hereof, and expressly incorporatedherein.

BACKGROUND

The present disclosure relates generally to satellite communications,and more specifically to systems and methods for dynamic antennaplatform offset calibration.

An Earth-based antenna terminal for communication with a satellitetypically has high antenna gain and a narrow beam pointed at thesatellite, because of the large distance to the satellite and to avoidinterference with other satellites. Mobile terminals on mobile vehiclesmay include an antenna system having a positioner to maintain pointing(or tracking) of the beam of the antenna system at the satellite duringmovement of the mobile vehicle.

Pointing error (e.g., misalignment) between a direction of maximum gainof the beam of the antenna and the actual direction from the antenna tothe satellite can have a detrimental effect on the quality of thecommunication link between the antenna and the satellite. Relativelysmall misalignment may be compensated for by reducing a modulation andcoding rate of signals communicated between the antenna system and thesatellite. However, to maintain a given data rate (e.g., bits-per-second(bps)), this approach may increase system resource usage and thus resultin inefficient use of the resources. Pointing error can also beassociated with challenges in ensuring compliance with interferencerequirements with other satellites that are imposed by regulatoryagencies (e.g., Federal Communications Commission (FCC), InternationalTelecommunication Union (ITU), etc.) and/or a coordination agreementwith operators of the other satellites.

Pointing error associated with an antenna system mounted to a mobilevehicle may result from misalignment between a sensor (e.g., an inertialreference unit (IRU)) of the mobile vehicle and the antenna system(e.g., a mounting platform of the antenna system), which may be referredto as antenna platform misalignment. Antenna platform misalignment maybe caused by manufacturing tolerances between the sensor and the antennasystem, structural deflections caused by movement and otherdisturbances, and other factors. In order to compensate for pointingerror, whether associated with antenna platform misalignment or otherfactors, the mobile antenna terminal may perform a signal-basedmispointing correction operation such as peaking, conical scan, sinescan, and similar methods. However, mispointing correction operationsmay not properly correct for antenna platform misalignment in all beamdirections. Further, the mispointing correction operations may require adedicated calibration routine that inhibits user communications, and mayrequire the mobile vehicle to be pointed in orientations associated withthe calibration routine.

SUMMARY

In one embodiment, a method is described for providing dynamic antennaplatform offset calibration. The method includes communicating, at amobile vehicle according to a first tracking mode during one or moretravel segments of the mobile vehicle, first user data with a targetsatellite via a beam of an antenna mounted to the mobile vehicle,wherein communicating the first user data according to the firsttracking mode includes performing an alignment calibration procedure todetermine an antenna pointing offset based at least in part on adifference between an estimated pointing direction from the antenna tothe target satellite that is determined based at least in part onpositional information of the mobile vehicle and a peaked pointingdirection from the antenna to the target satellite that is determinedbased at least in part on a measured signal characteristic of the firstuser data communicated during the alignment calibration procedure. Insome examples, communicating the first user data according to the firsttracking mode may also include pointing the beam of the antenna towardsthe target satellite for subsequent communication of the first user databased at least in part on the positional information of the mobilevehicle and the determined antenna pointing offset. The method includesrepeating the alignment calibration procedure until determining that thealignment calibration procedure has been performed for a plurality ofspatial conditions that satisfy a spatial separation criteria, anddetermining, for each of the calibration procedures performed for theplurality of spatial conditions, a respective calibration vector setbased at least in part on the respective peaked pointing directionassociated with the respective one of the plurality of spatialconditions. The method also includes determining, based at least in parton determining that the alignment calibration procedure has beenperformed for the plurality of spatial conditions that satisfy thespatial separation criteria, an antenna platform offset between areference frame of the antenna and a reference frame of the mobilevehicle based at least in part on the calibration vector sets determinedfor each of the calibration procedures performed for the plurality ofspatial conditions, and communicating, subsequent to the determining ofthe antenna platform offset, second user data with the target satellitevia the beam of the antenna according to a second tracking mode, whereincommunicating the second user data according to the second tracking modecomprises pointing the beam of the antenna towards the target satellitefor communicating the second user data based at least in part on thepositional information of the mobile vehicle and the determined antennaplatform offset.

The foregoing has outlined rather broadly the features of an exampleaccording to the disclosure in order that the detailed description thatfollows may be better understood. Additional features and advantageswill be described hereinafter. The conception and specific examplesdisclosed may be readily utilized as a basis for modifying or designingother methods or apparatuses for carrying out the same purposes of thepresent disclosure. Such equivalent constructions do not depart from thescope of the appended claims. Characteristics of the concepts disclosedherein, both their organization and method of operation, together withassociated advantages will be better understood from the followingdescription when considered in connection with the accompanying figures.Each of the figures is provided for the purpose of illustration anddescription only, and not as a definition of the limits of the claims.

BRIEF DESCRIPTION OF THE DRAWINGS

A further understanding of the nature and advantages of the presentdisclosure may be realized by reference to the following drawings. Inthe appended figures, similar components or features may have the samereference label. Further, various components of the same type may bedistinguished by following the reference label by a dash and a secondlabel that distinguishes among the similar components. If only the firstreference label is used in the specification, the description isapplicable to any one of the similar components having the same firstreference label irrespective of the second reference label.

FIG. 1 illustrates an example satellite communications system thatsupports dynamic antenna platform offset calibration in accordance withaspects of the present disclosure;

FIG. 2 is a block diagram illustrating an example of an antenna systemmounted on a mobile vehicle for communications with a target satellite,that supports dynamic antenna platform offset calibration in accordancewith aspects of the present disclosure;

FIG. 3 illustrates perspective view of an example of an antenna and apositioner that supports dynamic antenna platform offset calibration inaccordance with aspects of the present disclosure;

FIG. 4 is an illustration showing a global reference frame, a mobilevehicle reference frame, and an antenna reference frame that may be usedto support dynamic antenna alignment offset calibration in accordancewith aspects of the present disclosure;

FIG. 5 illustrates an example of a method for dynamic antenna platformoffset calibration in accordance with aspects of the present disclosure;

FIG. 6 illustrates a block diagram of an apparatus that supports dynamicantenna platform offset calibration in accordance with aspects of thepresent disclosure; and

FIG. 7 illustrates a block diagram of an apparatus that supports dynamicantenna platform offset calibration in accordance with aspects of thepresent disclosure.

DETAILED DESCRIPTION

Systems and methods are described herein for supporting dynamic antennaplatform offset calibration for an antenna system mounted to a mobilevehicle. In particular, aspects of dynamic antenna platform offsetcalibration in accordance with the present disclosure can be performedwhile communicating user data associated with the mobile vehicle (e.g.,based at least in part on alignment calibration procedures includingmeasurements of user data signals), with an antenna platform offsetbeing updated when alignment calibration procedures have been performedat suitably separated spatial conditions. Accordingly, antenna platformoffset calibration in accordance with the present disclosure may beperformed throughout the operation of the mobile vehicle withoutrequiring that the vehicle be proactively aligned in a particularorientation for a dedicated calibration routine prior to using theantenna for communicating user data during normal operation of themobile vehicle.

This description provides examples, and is not intended to limit thescope, applicability or configuration of embodiments of the principlesdescribed herein. Rather, the following description will provide thoseskilled in the art with an enabling description for implementingembodiments of the principles described herein. Various changes may bemade in the function and arrangement of elements.

Thus, various embodiments may omit, substitute, or add variousprocedures or components as appropriate. For instance, it should beappreciated that the methods may be performed in an order different thanthat described, and that various steps may be added, omitted orcombined. Also, aspects and elements described with respect to certainembodiments may be combined in various other embodiments. It should alsobe appreciated that the following systems, methods, devices, andsoftware may individually or collectively be components of a largersystem, wherein other procedures may take precedence over or otherwisemodify their application.

FIG. 1 illustrates an example satellite communications system 100 thatsupports dynamic antenna platform offset calibration in accordance withaspects of the present disclosure. The satellite communications system100 includes a mobile vehicle 102 having an antenna system 150 thatsupports wireless communications with a satellite (e.g., a targetsatellite 110). Other configurations for supporting dynamic antennaplatform offset calibration may have more or fewer components than thesatellite communications system 100 of FIG. 1.

In the illustrated embodiment, the target satellite 110 providesbidirectional communication between the mobile vehicle 102 and a gatewayterminal 130. The gateway terminal 130 may be referred to as a hub orground station. The gateway terminal 130 includes an antenna thatsupports transmitting forward uplink signals 140 to the target satellite110 and receiving return downlink signals 142 from the target satellite110. The gateway terminal 130 can also schedule traffic communicated viathe antenna system 150. Alternatively, the scheduling can be performedin other parts of the satellite communications system 100 (e.g., a corenode, or other components, not shown). Forward uplink signals 140 and/orreturn downlink signals 142 communicated between the gateway terminal130 and the target satellite 110 can use the same, overlapping, ordifferent frequencies as the forward downlink signals 114 and/or returnuplink signals 116 communicated between the target satellite 110 and theantenna system 150.

The gateway terminal 130 can be provided as an interface between anetwork 135 and the target satellite 110. The gateway terminal 130 canbe configured to receive data and information directed to the antennasystem 150 from a source accessible via the network 135. The gatewayterminal 130 can format the data and information and transmit forwarduplink signals 140 to the target satellite 110 for delivery to theantenna system 150. Similarly, the gateway terminal 130 can beconfigured to receive return downlink signals 142 from the targetsatellite 110 (e.g., containing data and information originating fromthe antenna system 150) that is directed to a destination accessible viathe network 135. The gateway terminal 130 can also format the receivedreturn downlink signals 142 for transmission on the network 135.

The network 135 can be any type of network and can include for example,the Internet, an IP network, an intranet, a wide area network (WAN), avirtual LAN (VLAN), a fiber optic network, a cable network, a publicswitched telephone network (PSTN), a public switched data network(PSDN), a public land mobile network, and/or any other type of networksupporting communication between devices as described herein. Thenetwork 135 can include both wired and wireless communications links aswell as optical links. The network 135 can connect multiple gatewayterminals 130 that can be in communication with target satellite 110and/or with other satellites.

The target satellite 110 can receive the forward uplink signals 140 fromthe gateway terminal 130 and transmit corresponding forward downlinksignals 114 to the antenna system 150. The target satellite 110 can alsoreceive return uplink signals 116 from the antenna system 150 andtransmit corresponding return downlink signals 142 to the gatewayterminal 130. The target satellite 110 can operate in a multiple spotbeam mode, transmitting and receiving a number of narrow beams directedto different regions on Earth. Alternatively, the target satellite 110can operate in wide area coverage beam mode, transmitting one or morewide area coverage beams. In various embodiments the target satellite110 may be a geostationary satellite or a non-geostationary satellite,such as a low earth orbit (LEO) or medium earth orbit (MEO) satellite.Although only a single target satellite 110 is shown in the satellitecommunications system 100, other communications system may have morethan one target satellite 110, and the more than one target satellites110 may support various operations of unidirectional or bidirectionalcommunications, including the operations of dynamic antenna platformoffset calibration described herein.

The target satellite 110 can be configured as a “bent pipe” satellitethat performs frequency and polarization conversion of the receivedsignals before retransmission of the signals to their destination. Asanother example, the target satellite 110 can be configured as aregenerative satellite that demodulates and remodulates the receivedsignals before retransmission.

The antenna system 150 is mounted on the mobile vehicle 102, which is anairplane in the illustrated example. More generally, an antenna system150 can be mounted on various types of mobile vehicles 102 such asaircraft (e.g., airplanes, helicopters, drones, blimps, balloons, etc.),trains, automobiles (e.g., cars, trucks, busses, etc.), watercraft(e.g., private boats, commercial shipping vessels, cruise ships, etc.)and others.

In some embodiments described herein the antenna system 150 is used forbidirectional (two-way) communication with the target satellite 110. Inother embodiments, the antenna system 150 may be used for unidirectionalcommunication with the target satellite 110, such as a receive-onlyimplementation (e.g., receiving satellite broadcast television).Although only one antenna system 150 is illustrated in FIG. 1, othersatellite communications systems that support dynamic antenna platformoffset calibration may include more than one mobile vehicle 102 havingan antenna system 150, or one or more mobile vehicles 102 having morethan one antenna system 150.

The antenna system 150 includes an antenna 152 associated with a beam155 that supports communication between the mobile vehicle 102 and thetarget satellite 110. In the illustrated embodiment, the antenna 152includes an array of waveguide antenna elements arranged in arectangular panel. Each of the antenna elements can include awaveguide-type feed structure including a horn antenna. Alternatively,the antenna 152 may be a different type of antenna, such as a reflectorantenna, a phased array antenna, a slot array antenna, etc.

The beam 155 of antenna 152 that is pointed towards the target satellite110 has sufficient antenna gain in the direction of the target satellite110 to permit communication of one or more signals. The communicationcan be bidirectional (e.g., by the antenna 152 transmitting a signal tothe target satellite 110 and also receiving a signal from the targetsatellite 110) or unidirectional (e.g., the antenna 152 eithertransmitting a signal to the target satellite 110 or receiving a signalfrom the target satellite 110, but not both).

The antenna system 150 also includes a positioner 153 for pointing thebeam 155 towards the target satellite 110 (e.g., along an estimate of analigned direction from the antenna 152 to the target satellite 110,which may be referred to a satellite look angle) using the techniquesdescribed herein. In the example of antenna system 150, the positioner153 includes an alignment mechanism responsive to a control signal froman antenna control unit (ACU) (not shown) to provide pointing of thebeam 155 towards the target satellite 110 about two rotational degreesof freedom (e.g., elevation and azimuth). In some examples the antenna152 may include a phased array of antenna elements, and a positioner 153for pointing the beam 155 towards the target satellite 110 may includean electronic beamformer (not shown) that forms the beam 155 via thephased array of antenna elements by applying phase and/or amplitudeshifting of signals communicated by respective antenna elements of thephased array. In some examples in accordance with the presentdisclosure, an antenna system 150 may include one or more positioners153 that collectively provide both a mechanical positioning and anelectronic beamforming.

Based on the location of the target satellite 110, the location of themobile vehicle 102, and the attitude (e.g., yaw, roll, and pitch) of themobile vehicle 102, the ACU of the antenna system 150 may determine andprovide a control signal to the positioner 153 to maintain pointing ofthe beam 155 at the target satellite 110 as the mobile vehicle 102and/or the target satellite 110 moves. In some cases, the direction ofmaximum gain of the beam 155 may be aligned with the direction of thetarget satellite 110. Alternatively, the gain of the beam 155 in thedirection from the antenna 152 to the target satellite 110 may be lessthan the maximum gain of the beam 155, due to the direction of maximumgain being aligned in a direction different from the direction to thetarget satellite 110. In various examples the misalignment may be due topointing accuracy limitations of the antenna 152, offsets in sensors ofthe mobile vehicle 102, offsets of the antenna system 150, or an antennaplatform misalignment (e.g., an alignment difference between a sensor ofthe mobile vehicle 102 and the antenna system 150). The differencebetween the direction of maximum gain of the beam 155 and the directionfrom the antenna 152 to the target satellite 110 is referred to hereinas the pointing error.

In accordance with aspects of the present disclosure, the antenna system150 (e.g., as directed by an alignment calibration controller) mayperform alignment calibration procedures associated with differentspatial conditions while the antenna system 150 is communicating userdata during travel segments of the mobile vehicle 102. The alignmentcalibration procedures at the different spatial conditions may be usedto determine an antenna platform offset in order to compensate forantenna platform misalignment. As used herein, a spatial condition mayrefer to a spatial position and/or orientation of the antenna 152, themobile vehicle 102, or both. For example, a spatial condition may referto one or more of an antenna azimuth direction, an antenna elevationdirection, a mobile vehicle heading (e.g., yaw angle), a mobile vehicleroll angle, a mobile vehicle pitch orientation, a relative positionbetween an antenna 152 and a mobile vehicle 102, or others. Thealignment calibration controller may determine the antenna platformoffset based on the alignment calibration procedures for the differentspatial conditions when the different spatial conditions collectivelysatisfy a spatial separation criteria.

An alignment calibration procedure in accordance with the presentdisclosure may include sweeping the beam 155 in different directionswhile communicating with the target satellite 110, and measuring asignal characteristic associated with the communications at thedifferent directions. By sweeping the beam 155 in different directionswhile communicating with the target satellite 110, the alignmentcalibration controller can determine an orientation of the beam 155associated with a peak value of the measured signal characteristic.

For example, the alignment calibration controller may first estimate analigned pointing direction from the antenna 152 to the target satellite110 based on the location of the antenna 152 (e.g., provided as anapproximation from a GPS location of the antenna system 150 or from aGPS location of another point of the mobile vehicle 102), the locationof the target satellite 110 (e.g., as provided by a previouslydetermined orbital position and stored at the mobile vehicle 102, from alocation signal received from the target satellite 110 or some othersource, or from a value calculated by the ACU based on an understoodorbital path of the target satellite 110), and the attitude of themobile vehicle 102 (e.g., as provided by the inertial reference unit(IRU) of the mobile vehicle 102). In some examples the location of theantenna 152 or the attitude of the mobile vehicle 102 may be referred toas positional information of the mobile vehicle 102. To support thealignment calibration procedure, the ACU may then determine misaligneddirections that are different from the estimated aligned direction(e.g., as offset from the aligned direction by an angular increment),and cause the beam 155 to be pointed in the misaligned directions duringcommunications with the target satellite 110. The antenna system 150, orsome other supporting component (e.g., a modem) may measure a signalcharacteristic (e.g., a signal strength or a signal quality) of userdata communicated at the respective misaligned directions of the beam155.

In other examples of an alignment calibration procedure in accordancewith the present disclosure, the alignment calibration controller maycause incremental changes in orientation of the beam 155 (e.g.,incremental changes in antenna azimuth and/or elevation) using themeasured signal characteristic and without explicitly basing thepointing directions during the alignment calibration procedure on anestimate of the aligned direction determined from the location andattitude information. By omitting the estimation of an aligneddirection, such alignment calibration procedures may not necessarily bebased on the location of the antenna 152, the location of the targetsatellite 110, or the attitude of the mobile vehicle 102. Rather, suchalignment calibration procedures may instead determine whether signalstrength or signal quality associated with the communicated user dataincreased or decreased in response to the change in orientation of thebeam 155 in order to determine a direction associated with a peak signalcharacteristic.

Accordingly, while supporting user data communications via the beam 155of the antenna 152 at the misaligned directions (e.g., without requiringinhibiting transmissions of the antenna 152, or while receivingtransmissions from the target satellite 110 via the antenna 152), thealignment calibration controller may measure, or receive a measurementof a signal strength or a signal quality for the respective misaligneddirections, and determine a “peaked” direction associated with thehighest signal strength or signal quality of the user data. Theorientation of the beam 155 when peaked may be determined based on theoutput from an antenna positioning motor or sensors (e.g., positional orangular encoders associated with a positioning mechanism) used to assistin physically positioning the antenna 152 (e.g., directing the boresightof the antenna 152 to the target satellite 110), or by a beamformer usedto form the beam 155 from a plurality of antenna elements of a phasedarray (e.g., a calculation of an orientation of the beam 155 used todetermine signal phase and amplitude adjustments for forming the beam155). For example, in one embodiment in which the antenna 152 ispositioned using antenna positioning motors supporting motion in anazimuth direction and in an elevation direction, the azimuth andelevation that result in the antenna 152 receiving the strongest signalare used as the peaked orientation of the beam 155. The differencebetween the estimated aligned direction between the beam 155 and thetarget satellite 110 and the peaked direction between the beam 155 andthe target satellite 110 may be calculated as an antenna pointingoffset, which may then be applied to subsequent pointing operations(e.g., for subsequent communication of user data or for subsequentalignment calibration procedures) by the alignment calibrationcontroller to more accurately orient the beam 155 towards the targetsatellite 110.

Although such peaking operations may provide suitable beam pointingcalibration within a similar range of spatial conditions (e.g., asimilar orientation of the beam 155 in an azimuth direction of theantenna 152), the antenna pointing offset may not be suitable for otherspatial conditions of the antenna system 150 (e.g., other azimuthorientations of the beam 155 in the azimuth direction of the antenna152). For example, the antenna system 150 may be installed with anantenna platform misalignment between the antenna system 150 and asensor of the mobile vehicle 102 (e.g., an IRU of the mobile vehicle102), which in some examples may correspond to rotational offsetsbetween the sensor of the mobile vehicle 102 and the antenna system 150(e.g., a roll offset, a pitch offset, and/or a yaw offset). Thus, anantenna platform misalignment may be associated with three or moredegrees of freedom, whereas an alignment calibration procedure (e.g., acalibration procedure to compensate for an azimuth offset and anelevation offset of the antenna system 150 at a particular spatialcondition) may only compensate for two degrees of freedom. Accordingly,when the antenna system 150 is installed on the mobile vehicle 102 withan antenna platform misalignment, a determined antenna pointing offset(e.g., an elevation offset and an azimuth offset) that improves antennaalignment at a given azimuth orientation of the beam 155 may degradealignment of the beam 155 of the antenna 152 at a different azimuthorientation of the beam 155 (e.g., an opposite azimuth orientation ofthe beam 155).

Although alignment calibration procedures may be performed whilecommunicating user data, the data rate supported by the antenna system150 may be degraded while performing an alignment calibration procedure.For example, when pointing the beam 155 along the misaligned directionsof an alignment calibration procedure, the gain of the antenna 152 maybe reduced as a result of a lower gain portion of the beam 155 beingaligned with the target satellite. Although the lower gain portion ofthe beam 155 may still support user data communication, the antennasystem 150 may employ a reduced modulation and coding rate (e.g., areduced modulation and coding scheme (MCS)) in order to provide reliablecommunication via the antenna 152 that is operating with the lower gain.Thus, in accordance with aspects of the present disclosure, theperiodicity of performing alignment calibration procedures to supportdynamic antenna platform offset calibration may be extended (e.g.,performing alignment calibration procedures less often) upon determiningand/or refining an antenna platform offset. Further, alignmentcalibration procedures to support dynamic antenna platform offsetcalibration may be scheduled more often when requested data rates arerelatively low (e.g., when a reduced MCS would not impede the requesteddata rate), or may be scheduled less often or even postponed whenrequested data rates are relatively high (e.g., when a reduced MCS wouldimpede the requested data rate).

In accordance with aspects of the present disclosure, a first trackingmode may be employed upon the mobile vehicle 102 entering service. Thefirst tracking mode may track the target satellite 110 using positionalinformation (e.g., a position of the target satellite 110, a position ofthe mobile vehicle 102, and an attitude of the mobile vehicle 102), andantenna pointing offsets determined from alignment calibrationprocedures conducted while communicating user data. For example, anestimated aligned pointing direction for the beam 155 may be determinedbased on the inertial reference information of the mobile vehicle 102,which may serve as the starting point or center point of an alignmentcalibration procedure that determines an antenna pointing offset forupdating the estimated aligned pointing direction for the next alignmentcalibration procedure (which may immediately follow the previous one orbe separated by a short period of pointing using the estimated alignedpointing direction).

As the alignment calibration procedures are performed at various spatialconditions, an alignment calibration controller may identify that thevarious spatial conditions meet a spatial separation criteria forapplying the results of the alignment calibration procedures todetermine the antenna platform misalignment (e.g., within calibrationbins associated with different ranges of spatial conditions, whichensures a degree of spatial separation between the stored results ofalignment calibration procedures associated with spatial conditions).Results from the alignment calibration procedure performed at each ofthe identified spatial conditions may be stored in memory (e.g.,memory/storage associated with the alignment calibration controller),which may include a calibration vector set associated with the alignmentcalibration procedure for each of the identified spatial conditions.Upon alignment calibration procedures being performed during user datacommunications at a plurality of spatial conditions that satisfy aspatial separation criteria (e.g., satisfying a threshold distributionof azimuth directions of the antenna 152, or a threshold distribution ofheading directions of the mobile vehicle 102), an antenna platformoffset may be determined by the alignment calibration controller, basedon the results from the alignment calibration procedures, to compensatefor antenna platform misalignment. Subsequently, the antenna may bepointed (e.g., by the ACU) according to a second tracking mode that isbased at least in part on the positional information of the mobilevehicle 102 and the determined antenna platform offset.

In various examples, the first tracking mode may be based at least inpart on a “zero” antenna platform offset (e.g., assuming that the sensorof the mobile vehicle 102 and the antenna system 150 are installed in analigned orientation with zero antenna platform misalignment, either asan explicit antenna platform offset having values of zero, or a lack ofan antenna platform offset with empty or null values), a manual antennaplatform offset (e.g., an antenna platform misalignment that wasphysically measured between the antenna system 150 and the mobilevehicle 102, or an antenna platform misalignment that was estimatedbased on a statistical distribution of antenna platform misalignments ofmultiple mobile vehicles 102, and stored at the ACU). Thus, the methodsand apparatus described herein may support determining an initialantenna platform offset between the antenna system 150 and the mobilevehicle 102.

In various examples the antenna system 150 may continue performingalignment calibration procedures (e.g., as directed by the alignmentcalibration controller) during ongoing operation of the mobile vehicle102 in the second tracking mode, and upon performing alignmentcalibration procedures at another set of spatial conditions that satisfya spatial separation criteria, the alignment calibration controller maydetermine an updated antenna platform offset. In other words, themethods and apparatus described herein may also support providingongoing refinement to the antenna platform offset between the antennasystem 150 and the mobile vehicle 102.

The described operations may eliminate the need to perform a dedicatedcalibration routine for determining an antenna platform offset,including those where the mobile vehicle 102 is positioned in particularorientations, and may also eliminate the need to inhibit communicationswhile performing calibration procedures to determine an antenna platformoffset, because the alignment calibration procedures may be based atleast in part on measurements performed on communicated user data.

FIG. 2 is a block diagram 200 illustrating an example of an antennasystem 150-a mounted on a mobile vehicle 102-a for communications with atarget satellite 110-a, that supports dynamic antenna platform offsetcalibration in accordance with aspects of the present disclosure. Theantenna system 150-a, the mobile vehicle 102-a, and the target satellite110-a may each be examples of the respective components described withreference to FIG. 1. In the illustrated example, the components of theantenna system 150-a are distributed between a mobile vehicle interior201 and a radome 202 (e.g., mounted to the exterior of a mobile vehicle102), and certain aspects of the operation of the antenna system 150-amay be managed by an ACU 270 (e.g., of the antenna system 150-a). Otherconfigurations of an antenna system 150 that supports dynamic antennaplatform offset calibration having more or fewer components than theexample antenna system 150-a are possible, and the components may bearranged in different locations of the mobile vehicle 102-a. Moreover,the functionalities described herein can be distributed among thecomponents in a different manner than described herein.

The antenna system 150-a includes an antenna 152-a that is housed underthe radome 202, which may be disposed on the top of the body or otherlocation (e.g., on the tail, etc.) of the mobile vehicle 102-a. Theantenna 152-a is associated with a beam 155-a that may supporttransmission of a return uplink signal and/or reception of a forwarddownlink signal (e.g., return uplink signal 116 and/or forward downlinksignal 114 as described with reference to FIG. 1) to support one-way ortwo-way data communication between a network and the mobile vehicle102-a and/or data devices 260 associated with (e.g., within) the mobilevehicle 102-a. The data devices 260 can include mobile devices (e.g.,smartphones, laptops, tablets, netbooks, and the like) such as personalelectronic devices (PEDs) brought onto the mobile vehicle 102-a bypassengers. In some examples, the data devices 260 can include a portionof the mobile vehicle 102-a itself, such as passenger seat-back systemsor other devices on the mobile vehicle 102-a.

The data devices 260 can communicate with network access unit 240 via acommunication link that can be wired or wireless. The communicationlinks can be, for example, part of a local area network such as awireless local area network (WLAN) supported by wireless access point(WAP) 250. One or more WAPs 250 can be distributed about the mobilevehicle 102-a, and can, in conjunction with network access unit 240,provide traffic switching or routing functionality. The network accessunit 240 can also allow passengers to access one or more servers (notshown) local to the mobile vehicle 102-a, such as a server on anairplane that provides in-flight entertainment.

In operation, the network access unit 240 can provide uplink datareceived from the data devices 260 to modem 230 to generate modulateduplink data (e.g., a transmit intermediate frequency (IF) signal) fordelivery to transceiver 210, where one or both of the modem 230 and thetransceiver 210 may be a part of the antenna system 150-a, or otherwiseinterface with the antenna system 150-a. The transceiver 210 canupconvert and amplify the modulated uplink data to generate a returnuplink signal (e.g., return uplink signal 116 described with referenceto FIG. 1) for transmission to the target satellite 110-a via theantenna 152-a. The transceiver 210 can also receive a forward downlinksignal (e.g., forward downlink signal 114 described with reference toFIG. 1) from the target satellite 110-a via the antenna 152-a. Thetransceiver 210 can amplify and downconvert the forward downlink signalto generate modulated downlink data (e.g., a receive IF signal) fordemodulation by the modem 230. The demodulated downlink data from themodem 230 can then be provided to the network access unit 240 forrouting to the data devices 260. The modem 230 can be integrated withthe network access unit 240, or can be a separate component, in someexamples. In the illustrated embodiment, the transceiver 210 is locatedoutside the body of the mobile vehicle 102-a and under the radome 202.Alternatively, the transceiver 210 can be located in a differentlocation, such as within the mobile vehicle interior 201.

In some examples the antenna system 150-a may include a positioner 153-acoupled to the antenna 152-a, which may be an example of a positioningmechanism for physically pointing the beam 155-a of the antenna 152-a.(e.g., when the direction of highest gain of the beam 155-a of theantenna 152-a is fixed relative to the aperture of the antenna 152-a).For example, the antenna 152-a may be a direct radiating two-dimensionalarray which results in an antenna boresight being normal to a planecontaining the antenna elements of the array. As another example, theantenna 152-a may be a reflector antenna, and the feed elements and/orthe reflector of the antenna 152-a can be mechanically steered by thepositioner 153-a to point the beam 155-a at the target satellite 110-a.In some examples the positioner 153-a may be an elevation-over-azimuth(EL/AZ), two-axis positioner that provides adjustment of the beam 155-ain azimuth and elevation. In some examples the positioner 153-a may be athree-axis positioner to provide adjustment in azimuth, elevation, andskew. The positioner 153-a may be responsive to a control signal 272-afrom ACU 270 to mechanically point the beam 155-a of the antenna 152-ain the direction of the target satellite 110-a as the mobile vehicle102-a and/or the target satellite 110-a moves.

In some examples the antenna system 150-a may include a positioner 153-bcoupled between the modem 230 and the transceiver 210, which may be anexample of a beamformer for electronically directing the beam 155-a. Forexample, the antenna 152-a may be a non-movable, fully electronicscanned phased array antenna. In such a case, the positioner 153-a caninclude feed networks and phase controlling devices to properly phasesignals communicated with some or all of the antenna elements of theantenna 152-a to steer the beam (e.g., in azimuth and elevation). Thepositioner 153-b may be responsive to a control signal 272-b from ACU270 to electronically point the beam 155-a of the antenna 152-a in thedirection of the target satellite 110-a as the mobile vehicle 102-aand/or the target satellite 110-a moves.

In some examples the antenna system 150-a may include both positioner153-a and positioner 153-b. For example, the antenna 152-a may be anelectro-mechanically steered array such as a variably inclinedcontinuous transverse stub (VICTS) antenna, which may include onemechanical scan axis supported by the positioner 153-a, and oneelectrical scan axis supported by the positioner 153-b. Alternatively,the antenna system 150-a may include other positioners 153 that may varyfrom embodiment to embodiment, and may depend on the antenna type of theantenna 152-a.

Accordingly, the control signals 272-a and/or 272-b may adjust theangular direction of the beam 155-a depending on the manner in which thepositioner(s) 153 are controlled, and can vary from embodiment toembodiment. Although only a single control signal 272 is illustrated foreach of the positioners 153 shown in FIG. 2, “control signal,” as usedherein, can include one or more separate control signals provided by theACU 270 to the respective positioner 153, which in turn may be providedon one or more signaling connections. For example, in some embodimentsin which a positioner 153 adjusts the angular direction of the beam inmultiple axes (e.g., azimuth and elevation), the control signal includesa control signal indicating the angular value of each axis. Thefunctions of the ACU 270 can be implemented in hardware, instructionsembodied in memory and formatted to be executed by one or more generalor application specific processors, firmware, or any combinationthereof.

During operation, as the mobile vehicle 102-a moves relative to thetarget satellite 110-a, the ACU 270 may provide control signal(s) 272-aand/or 272-b to positioner 153-a and/or positioner 153-b, respectively,to point the beam 155 of the antenna 152-a in the direction of thetarget satellite 110-a. The ACU 270 may determine the appropriateangular alignment based on the location of the target satellite 110-a,the location of the mobile vehicle 102-a, and the attitude (e.g., yaw,roll, and pitch) of the mobile vehicle 102-a. The ACU 270 may, forexample, store or otherwise obtain data indicating the location of thetarget satellite 110-a. The geographic location of the mobile vehicle102-a may, for example, be obtained via a global positioning system(GPS) 274 or other equipment associated with the mobile vehicle 102-a(e.g., from the IRU 280), including equipment located in the mobilevehicle interior 201, the radome 202, or any combination thereof. Theattitude of the mobile vehicle 102-a may, for example, be provided viathe IRU 280 of the mobile vehicle 102-a (e.g., as measured by a set ofgyroscopes of the IRU 280), which in some examples may be referred to aninertial measurement unit (IMU). In some examples both the location andattitude of the mobile vehicle 102-a may be provided by a singlecomponent (e.g., performing the functions of both the IRU 280 and theGPS 274) that may be referred to as a position and attitude measuringdevice (PAMD).

To reduce pointing error associated with aligning beam 155-a with thetarget satellite 110-a, the ACU 270 may provide control signal 272-band/or control signal 272-b in accordance with alignment calibrationprocedures (e.g., as directed by an alignment calibration controller275) during the communication of user data for the data devices 260.Although the alignment calibration controller 275 is illustrated as partof the ACU 270 in the example of antenna system 150-a, in other examplesof an antenna system 150 an alignment calibration controller 275 may bepart of another component of an antenna system, such as part of a modem230. In other examples, an alignment calibration controller 275 may be astandalone component of an antenna system 150. In yet other examples,the structures and/or instructions associated with an alignmentcalibration controller 275 may be distributed between two or morecomponents of an antenna system 150 such as, for example, the ACU 270and the modem 230.

The antenna system 150-a (e.g., as directed by the alignment calibrationcontroller 275) may perform alignment calibration procedures associatedwith different spatial conditions while the antenna system 150-a iscommunicating user data during travel segments of the mobile vehicle102-a. When it is determined (e.g., by the alignment calibrationcontroller 275) that alignment calibration procedures have beenperformed for a set of spatial conditions that satisfy a spatialseparation criteria, information from the alignment calibrationprocedures (e.g., calibration vector sets) may be used to determine anantenna platform offset, associated with the antenna platformmisalignment between the mobile vehicle 102-a (e.g., the orientation ofthe IRU 280, or an adjusted output of the IRU 280) and the antenna 152-a(e.g., the reference frame of the antenna 152-a).

In various examples, the alignment calibration controller 275 may obtaina measured characteristic of the communicated user data to support thealignment calibration procedure performed at each of the set of spatialconditions. For example, the alignment calibration controller 275 mayobtain a received signal strength indicator (RSSI), a signal strengthindicator, a signal-to-noise ratio (SNR), or a combination thereof fromthe transceiver 210, the modem 230, or some other component indicatingthe signal characteristic of a forward downlink signal received by theantenna 152-a at various angular directions during a sweep or searchperformed by the alignment calibration procedure. Additionally oralternatively, the alignment calibration procedure may use the signalstrength (or other signal metric) of a signal (e.g., the return uplinkdata signal) transmitted by the antenna 152-a to the target satellite110-a at various angular directions during the sweep or search. In suchan example, the alignment calibration controller 275 may obtain thevalue of the measured signal characteristic of the return uplink signalthat was received by the target satellite 110-a from the gatewayterminal (or other elements of a satellite communications system such asa core node, NOC, etc.) via the forward downlink signal, or thealignment calibration controller 275 may receive an indication of aportion of the return uplink signal associated with a peak signalcharacteristic measured elsewhere (e.g., at the target satellite 110-aor at a gateway terminal 130) that may be used by the alignmentcalibration controller 275 to determine the orientation of the beam155-a upon the antenna 152-a transmitting the portion of the returnuplink signal.

The alignment calibration controller 275 can then determine a peakedpointing direction for the beam 155-a (e.g., the angular orientationthat directs the highest gain of the beam 155-a towards the targetsatellite 110-a) based on the measured signal characteristic at thevarious angular positions. The alignment calibration controller 275 mayuse a variety of techniques to determine the peaked pointing direction.For example, the alignment calibration controller 275 may fit the signalcharacteristic measurements to a 2-D or 3-D curve depending upon thecorrection profile of the alignment calibration procedure, and thendetermine the direction corresponding to the maximum signal metric(e.g., maximum signal strength or maximum SNR). Alternatively, othertechniques may be used. The alignment calibration controller 275 canthen determine an antenna pointing offset to improve pointing of thebeam 155-a towards the target satellite 110-a, and may operate with theACU 270 (e.g., updating the antenna pointing offset used by the ACU 270)to provide a control signal to the positioner 153-a and/or thepositioner 153-b to adjust the orientation of beam 155-a towards thetarget satellite 110-a accordingly. The ACU 270 can provide furtheradjustments to the direction of the beam 155-a as the mobile vehicle102-a moves relative to the target satellite 110-a, based at least inpart on the antenna pointing offset determined by the respectivealignment calibration procedure.

In accordance with aspects of the present disclosure, alignmentcalibration procedures, such as those described herein, may be performedfor multiple spatial conditions (e.g., multiple azimuth orientations ofthe antenna 152-a, or multiple heading directions of the mobile vehicle102-a) in a first tracking mode, where orientation of the beam 155-a ata given spatial condition may be based on positional information fromthe IRU 280 and/or GPS 274 (e.g., position of the target satellite110-a, position of the mobile vehicle 102-a, and attitude of the mobilevehicle 102-a), and may also be based on an antenna pointing offsetdetermined from an alignment calibration procedure. Upon performingalignment calibration procedures during user data communications at aset of spatial conditions that satisfy a spatial separation criteria(e.g., satisfying a threshold distribution of azimuth directions of theantenna 152-a, or a threshold distribution of heading directions of themobile vehicle 102-a), an antenna platform offset may be determinedbased on the results of the alignment calibration procedures in order tocompensate for antenna platform misalignment. Subsequently, the antennamay be pointed according to a second tracking mode that is based atleast in part on the determined antenna platform offset.

FIG. 3 illustrates perspective view of an example 300 of an antenna152-c and a positioner 153-c (e.g., of an antenna system 150, not shown,which may be an example of an antenna system 150 described withreference to FIGS. 1 and 2) that supports dynamic antenna platformoffset calibration in accordance with aspects of the present disclosure.In the example 300, the antenna 152-c includes an array 310 of antennaelements that may be a direct radiating two-dimensional array resultingin a boresight of the antenna 152-c being normal to a plane containingthe antenna elements of the array 310. Alternatively, the array 310 ofantenna elements can be arranged (e.g., in a non-planar arrangement) orfed (e.g., by a beamformer) in a different manner such that thedirection of highest gain of the antenna 152-c is not normal to theantenna elements of the array 310. As mentioned above, in otherembodiments in accordance with the present disclosure the antenna typeof the antenna 152-c may be different.

The positioner 153-c may be responsive to control signals provided by anACU 270 (e.g., as described with reference to FIG. 2) to point a beam155 of the antenna 152-c towards a target satellite 110. In theillustrated embodiment, the positioner 153-c is anelevation-over-azimuth (EL/AZ) two-axis positioner that providestwo-axis mechanical steering. The positioner 153-c includes a mechanicalazimuth adjustment mechanism to point the beam 155 of the antenna 152-cabout an azimuth axis 330, and a mechanical elevation adjustmentmechanism to point the beam 155 of the antenna 152-c about an elevationaxis 340. Each of the mechanical adjustment mechanisms may include amotor with gears and/or other elements to provide for movement of theantenna 152-c about the corresponding axis. As mentioned above, in otherembodiments the components used to point the beam 155 of the antenna152-c may be different.

The antenna 152-c may be mounted at a platform 320 to a mobile vehicle102, where the platform 320 may be coupled between the mobile vehicle102 and the positioner 153-c. The platform 320 may be associated with areference frame (e.g., an antenna reference frame) from which theorientation of a beam 155 of the antenna 152-c is measured. In otherwords, the platform 320 may provide a reference frame from which beamorientation is based (e.g., in elevation and azimuth). In variousexamples, the mobile vehicle 102 that the antenna 152-c is mounted tomay have a location provided for attaching the platform 320, such as apattern of holes to accept mechanical fasteners for securing theplatform 320 to the mobile vehicle 102.

The mounting location may be nominally prepared to provide a particularalignment between the platform 320 and a sensor (e.g., an IRU 280) ofthe mobile vehicle 102, such that the orientation of the beam 155 of theantenna 152-c may be provided with reference to the sensor of the mobilevehicle 102 (e.g., based at least in part on the measured roll, pitch,and yaw of the mobile vehicle 102). However, in various examples anantenna platform misalignment between the platform 320 and the sensor ofthe mobile vehicle 102 may result from manufacturing tolerances such asa planar skew of the mounting location for the platform 320, a planarskew of the surface of the platform 320 that mates with the mobilevehicle 102, hole size and/or positional variations associated with theplatform 320 and or the mounting location of the mobile vehicle 102,size variations of the fasteners used to secure the platform 320 to themobile vehicle 102, and/or other considerations. Further, in someexamples antenna platform misalignment may occur as a result ofdeflections of the mobile vehicle 102 between the platform 320 and thesensor of the mobile vehicle 102. Such antenna platform misalignment maycause pointing errors when pointing a beam 155 of the antenna 152-ctowards a target satellite 110. Thus, in accordance with aspects of thepresent disclosure, dynamic antenna platform offset calibration may beprovided in order to compensate for such antenna platform misalignment,and reduce or eliminate the pointing error associated with antennaplatform misalignment.

FIG. 4 is an illustration 400 showing a global reference frame 410, amobile vehicle reference frame 420, and an antenna reference frame 430that may be used to support dynamic antenna alignment offset calibrationin accordance with aspects of the present disclosure. The referenceframes may be used to describe positional information associated with atarget satellite 110-d and a mobile vehicle 102-d having an antennasystem 150-d, and an IRU 280-c, which may be examples of the relatedcomponents described with reference to FIGS. 1 through 3. For example,the global reference frame 410 may be used to identify a location of themobile vehicle 102-d and/or the target satellite 110-d. Further, theglobal reference frame 410, the mobile vehicle reference frame 420,and/or the antenna reference frame 430 may each be used to identify avector 405 from the antenna system 150-d to the target satellite 110-d.Although each of the reference frames of the illustration 400 aredescribed as three-dimensional reference frames having mutuallyorthogonal axes, one or more of a global reference frame, a mobilevehicle frame, or an antenna reference frame may be other types ofreference frames in other embodiments of dynamic antenna platform offsetcalibration.

The global reference frame 410 of the illustration 400 is an example ofa three-dimensional, topocentric Cartesian coordinate frame. The X axis411 of the global reference frame 410 may be aligned with the compassheading North. The Y axis 412 of the global reference frame 410 may bealigned with the compass heading East. The Z axis 413 of the globalreference frame 410 may be aligned with an earth radian that emanatesfrom the origin 415 of the global reference frame 410 and extendsthrough the center of the earth. The described alignment of the globalreference frame 410 may be referred to as a North, East, Down (NED)alignment. Each axis of the global reference frame 410 is orthogonal andforms a 90 degree angle with each of the other axes. In accordance withone embodiment of the present disclosure, the origin 415 of the globalreference frame 410 used by the IRU 280-c may be coincident with alatitude and longitude of the mobile vehicle 102-a. In various examplesthe altitude of the global reference frame 410 may assumed to be zero(e.g., the origin 415 of the global reference frame 410 is at an earthsurface, or an otherwise suitable reference elevation such as sealevel). In another example, the origin 415 of the global reference frame410 may be at the center of the earth, the Z axis 413 may be alignedwith the compass heading North, and the X axis 411 and the Y axis 412may each be aligned with a different earth longitude.

The mobile vehicle reference frame 420 may also be a three-dimensionalCartesian coordinate frame, and may be associated with the IRU 280-caboard the mobile vehicle 120-d. The X′ axis 421 of the mobile vehiclereference frame 420 may be aligned with the longitudinal axis (e.g.,from rear to front) of the mobile vehicle 102-d. The Y′ axis 422 of themobile vehicle reference frame 420 may be aligned with the lateral axis(e.g., from side to side) of the mobile vehicle 102-d. The Z′ axis 423of the mobile vehicle reference frame 420 may be aligned with thevertical axis (e.g., from top to bottom) of the mobile vehicle 102-d.Unlike the global reference frame 410, which remains fixed in attitudewith respect to earth, the mobile vehicle reference frame 420 movesalong with (e.g., is fixed with respect to) the mobile vehicle 102-d. Inother words, the origin 425 of the mobile vehicle reference frame 420may be fixed with respect to the mobile vehicle 102-d (e.g., at thelocation of the IRU 280-c).

The attitude of the mobile vehicle 102-d may be defined by the set ofrotations in roll, pitch and yaw between the mobile vehicle referenceframe 420 and the global reference frame 410. Roll of the mobile vehicle102-d may be defined as the rotation of the mobile vehicle 102-d aboutthe X′ axis 421 with reference to the X-Y plane of the global referenceframe 410 (e.g., as an angle between the Y′ axis 422 of the mobilevehicle reference frame 420 and the X-Y plane of the global referenceframe 410 when viewed along the X′ axis 421). Pitch may be defined asthe rotation of the mobile vehicle 102-d about the Y′ axis 422 withreference to the X-Y plane of the global reference frame 410 (e.g., asan angle between the X′ axis 421 of the mobile vehicle reference frame420 and the X-Y plane of the global reference frame 410 as viewed alongthe Y′ axis 422). Yaw may be defined as the direction of the X′ axis 421of the mobile vehicle reference frame 420 in the X-Y plane of the globalreference frame 410, which during level movement (e.g., level aircraftflight) may correspond to the rotation of the mobile vehicle 102-d aboutthe Z′ axis 423 of the mobile vehicle reference frame 420 or therotation of the mobile vehicle 102-d about the Z axis 413 of the globalreference frame 410.

In some examples, positional information indicating the attitude of themobile vehicle 102-d may be output from the IRU 280-c in the form ofthree angular displacements. A first angular displacement may representthe rotation in roll, the second may represent the rotation in pitch andthe third may represent the rotation in yaw. Although the mobile vehiclereference frame 420 is shown as aligned with the mobile vehicle 102-d,in some examples the mobile vehicle reference frame 420 may be offsetfrom the alignment with the mobile vehicle 102-d due to misalignmentbetween the mobile vehicle 102-d and the IRU 280-c. In some examples theIRU 280-c, or a controller associated with the mobile vehicle 102-d, maycompensate for such a misalignment through various calibrationoperations. In some examples, the IRU 280-c may, therefore, providevalues compensated for such misalignment between the IRU 280-c and themobile vehicle 102-c, such that the IRU 280-c provides attitude valuesin the mobile vehicle reference frame 420 despite a misalignment betweenthe IRU 280-c and the mobile vehicle 102-d. In other examples, the IRU280-c provides uncompensated values that are not in the mobile vehiclereference frame 420, and the uncompensated values are alternativelycorrected by the receiver of the values (e.g., an ACU 270 and/or analignment calibration controller 275).

The antenna reference frame 430 may also be a three-dimensionalCartesian coordinate frame, and may be associated with the antennasystem 150-d aboard the mobile vehicle 120-d. The X″ axis 431 of theantenna reference frame 430 may be aligned with the longitudinal axis ofthe antenna system 150-d. The Y″ axis 432 of the antenna reference frame430 may be aligned with the lateral axis of the antenna system 150-d.The Z″ axis 433 of the antenna reference frame 430 may be aligned withthe vertical axis of the antenna system 150-d. The antenna referenceframe 430 moves along with (e.g., is fixed with respect to) the antennasystem 150-d. In other words, the origin 435 of the antenna referenceframe 430 may be fixed with respect to the antenna system 150-d (e.g.,at the location of the antenna system 150-d).

The alignment of a beam 155 of the antenna system 150-d (e.g., along thevector 405) may be identified by the antenna system 150-d relative tothe antenna reference frame 430. For example, the antenna system 150-d(e.g., a positioner 153 of the antenna system 150-c) may point the beam155 along the vector 405 by way of a two-dimensional definition of theelevation and azimuth orientations of the vector 405 with respect to theantenna reference frame 430. Elevation of the vector 405 may be definedas an angle between the direction of the vector 405 and the X″-Y″ planeof the antenna reference frame 430. Azimuth of the vector 405 may bedefined as an angle between the direction of the vector 405 and the X″axis 431 when viewed in the X″-Y″ plane (e.g., an angle between the X″axis 431 and a projection of the vector 405 on the X″-Y″ plane).

In some examples the antenna system 150-d and the IRU 280-c may beinstalled on the mobile vehicle 102-d with a particular relativeorientation. For example, the antenna system 150-d may be installed onthe mobile vehicle 102-d such that the antenna reference frame 430 isnominally aligned with the mobile vehicle reference frame 420, such thatthe X′ axis 421 is aligned with the X″ axis 431, the Y′ axis 422 isaligned with the Y″ axis 432, and the Z′ axis 423 is aligned with the Z″axis 433. However, the actual alignment between the antenna referenceframe 430 and the mobile vehicle reference from 420 may be differentfrom the nominal alignment between the antenna reference frame 430 andthe mobile vehicle reference frame, which may be referred to as anantenna platform misalignment. In other words, for various reasonsincluding those described with reference to FIG. 3, the actualorientation of antenna reference frame 430 with respect to the mobilevehicle reference frame 420 may be different from a nominal orientationof the antenna reference frame 430 with respect to the mobile vehiclereference frame 420.

In order to communicate signals via the antenna system 150-d with themaximum signal strength, the antenna system 150-d (e.g., the ACU 270)may command a positioner 153 to align a beam 155 of the antenna system150-d in the direction of vector 405. The orientation of the vector 405can be calculated based on determined values or approximations for thelocation of the target satellite 110-d, the location of the antennasystem 150-d, and the attitude of the antenna system 150-d.

In some examples the location of the target satellite 110-d may be knownand available to the ACU 270 (e.g., from a position signal received bythe ACU 270, from a position value stored at the ACU 270, or as aposition determined by the ACU 270 based on orbital characteristics ofthe target satellite 110-d known by the ACU 270), and may be expressedin coordinates of the global reference frame 410. In some examples thelocation of the target satellite 110-d is provided to the ACU 270 from amodem 230 (e.g., a modem 230 as described with reference to FIG. 2)through an input port. In some embodiments, the origin of the referenceframe used to define the location of the target satellite 110-d (e.g., aGPS reference frame that identifies a location in terms of latitude,longitude, and elevation) will be displaced from the origin of theglobal reference frame 410, having an origin at the location of themobile vehicle 102-d, and the location of the target satellite 110-d maybe transformed into the global reference frame 410 (e.g., by the IRU280-c or the ACU 270).

In some examples the location of the antenna system 150-d may bedetermined at the antenna system 150-d, such as with a GPS receiver(e.g., GPS 274 described with reference to FIG. 2) that is substantiallyco-located with the antenna system 150-d and provides positionalinformation comprising the location of the antenna system 150-d. Inother examples the location of the antenna system 150-d may be assumedto be (e.g., approximated by) a location that is output by the IRU 280-cthat provides positional information comprising the location of the IRU280-c. In examples where the antenna system 150-d and the IRU 280-c arenot co-located, positional error due to the different assembly locationsof the IRU 280-c and the antenna system 150-d may be assumed to benegligible and ignored, or the positional differences may be known andcompensated for (e.g., by the ACU 270).

Based on the location of the target satellite 110-d and the antennasystem 150-d, a first unit vector {right arrow over (d)} can becalculated to represent the direction of the vector 405 in the globalreference frame 410. The first unit {right arrow over (d)} vector {rightarrow over (d)} may include three components, dx, dy, and dz, definedwith respect to the global reference frame 410 (e.g., along the X axis411, the Y axis 412, and the Z axis 413, respectively).

In general, the mobile vehicle 102-d may not have an attitude that isaligned with the global reference frame 410. That is, the mobile vehicle102-d may have a heading other than North, an angular pitch displacementrelative to the X-Y plane of the global reference frame 410, an angularroll displacement relative to the X-Y plane of the global referenceframe 410, or various combinations thereof. In such cases, the firstunit vector {right arrow over (d)} may be transformed using an aliastransformation, which generally transforms the representation of thefirst unit vector {right arrow over (d)} from a first reference frame toa second reference frame.

For reference frames comprising three-dimensional Cartesian coordinatesystems, the alias transformation of the first vector {right arrow over(d)} from a first reference frame to a second reference frame can becalculated as:

{right arrow over (d)} _(i) =M _(i) {right arrow over (d)}

where {right arrow over (d)} is the first unit vector in the firstreference frame, {right arrow over (d)}′_(i) the unit vector in thesecond reference frame and M_(i) is a rotation matrix. The rotationmatrix M_(i) may be calculated as:

$\begin{matrix}{{M_{i}\left( {R_{i},P_{i},Y_{i}} \right)} = \begin{bmatrix}{{\cos \left( P_{i} \right)}*{\cos \left( Y_{i} \right)}} & {{\cos \left( P_{i} \right)}*{\sin \left( Y_{i} \right)}} & {- {\sin \left( P_{i} \right)}} \\{{{\sin \left( R_{i} \right)}*{\sin \left( P_{i} \right)}*{\cos \left( Y_{i} \right)}} -} & {{{\sin \left( R_{i} \right)}*{\sin \left( P_{i} \right)}*{\sin \left( Y_{i} \right)}} +} & {{\sin \left( R_{i} \right)}*{\cos \left( P_{i} \right)}} \\{{\cos \left( R_{i} \right)}*{\sin \left( Y_{i} \right)}} & {{\cos \left( R_{i} \right)}*{\cos \left( Y_{i} \right)}} & \; \\{{{\cos \left( R_{i} \right)}*{\sin \left( P_{i} \right)}*{\cos \left( Y_{i} \right)}} +} & {{{\cos \left( R_{i} \right)}*{\sin \left( P_{i} \right)}*{\sin \left( Y_{i} \right)}} -} & {{\cos \left( R_{i} \right)}*{\cos \left( P_{i} \right)}} \\{{\sin \left( R_{i} \right)}*{\sin \left( Y_{i} \right)}} & {{\sin \left( R_{i} \right)}*{\cos \left( Y_{i} \right)}} & \;\end{bmatrix}} & (2)\end{matrix}$

where R_(i) is the roll offset between the first reference frame and thesecond reference frame, P_(i) is the pitch offset between the firstreference frame and the second reference frame, and Y_(i) is the yawoffset between the first reference frame and the second reference frame.Thus, the rotation matrix M_(i) may be used to perform the aliastransformation of the first unit vector {right arrow over (d)} in theglobal reference frame 410 to determine a corresponding second unitvector {right arrow over (d)}′_(i) representing the direction of thevector 405 in the mobile vehicle reference frame 420.

If both the location of the target satellite 110-d and the antennasystem 150-d are known and the antenna reference frame 430 is alignedwith the mobile vehicle reference frame 420, the second unit vector{right arrow over (d)}′_(i) from the antenna system 150-d to the targetsatellite 110-d in the mobile vehicle reference frame 420 could becalculated by applying Eq. 2 using the roll, pitch and yaw output fromthe IRU 280-c, which could then be used to determine an azimuth andelevation command to provide to a positioner 153 of the antenna system150-d. However, as described herein, the antenna system 150-d may bemounted to the mobile vehicle 102-d with an antenna platformmisalignment, such that the antenna system 150-d is not perfectlyaligned with the IRU 280-c. That is, the attitude in the antennareference frame 430 may be offset from the attitude of the mobilevehicle 102-d, which may cause pointing errors. In accordance withaspects of the present disclosure, dynamic antenna platform offsetcalibration may be performed to compensate for such antenna platformmisalignment, and the dynamic antenna platform offset calibration mayinclude alignment calibration procedures performed during various travelsegments of the mobile vehicle 102-d for a set of spatial conditions(e.g., antenna azimuth directions, mobile vehicle heading directions)that satisfy a spatial distribution threshold.

In one example of the alignment calibration procedure, the first unitvector {right arrow over (d)} from the antenna system 150-d to thetarget satellite 110-d (e.g., in the direction of vector 405) is firstcalculated in the global reference frame 410. For the purpose ofdetermining the first unit vector a, the difference between the locationof the IRU 280-c or the ACU 270 and the location of the antenna system150-d may be considered to be negligible, such that the location of theIRU 280-c or the location of the ACU 270 (e.g., as determined by a GPScollocated with the IRU 280-c or the ACU 270) may be used as anapproximation of the location of the antenna system 150-d. Further, anydifference in the location of the origin 415 of the global referenceframe 410 used to define the location of the target satellite 110-d andthe origin of the reference frame used to define the location of themobile vehicle 102-d (e.g., a location output of the IRU 280-c or thelocation output of the ACU 270, such as a GPS output in latitude,longitude, and elevation) may be managed by a translation of thecoordinates from one reference frame to the other. With a determinedlocation of the target satellite 110-d and a determined location of themobile vehicle 102-d being known in the global reference frame 410, thecalculation of the first unit vector {right arrow over (d)} isstraightforward.

Next, the first unit vector {right arrow over (d)} may be transformed byan alias transformation to the mobile vehicle reference frame 420 todetermine a second unit vector {right arrow over (d)}′_(i) in thedirection of the vector 405. This may be accomplished using the aliastransformation noted above in Eq. 1. The first unit vector {right arrowover (d)} is multiplied with the rotation matrix M_(i)(R_(i), P_(i),Y_(i)), of Eq. 2, where R_(i), may be the amount of roll as indicated bythe IRU 280-d, P_(i), may be the amount of pitch as indicated by the IRU280-d, and Y_(i) may be the amount of yaw as indicated by the IRU 280-d.

If the antenna reference frame 430 is aligned with the mobile vehiclereference frame 420 (e.g., if the antenna system 150-d is nominallyaligned with the IRU 280-d), the second unit vector {right arrow over(d)}′_(i) in the mobile vehicle reference frame 420 can be used directlyto determine azimuth and elevation of the antenna system 150-a (e.g., bythe ACU 270, for commanding the positioner 153). For example, azimuthand elevation may be generally identified in a particular referenceframe by the following equations:

$\begin{matrix}{\alpha_{i} = {\tan^{- 1}\left( \frac{{\overset{\rightarrow}{d}}_{iy}}{{\overset{\rightarrow}{d}}_{ix}} \right)}} & (3) \\{\epsilon_{i} = {\tan^{- 1}\left( \frac{- {\overset{\rightarrow}{d}}_{iz}}{\sqrt{\left( {\overset{\rightarrow}{d}}_{ix} \right)^{2} + \left( {\overset{\rightarrow}{d}}_{iy} \right)^{2}}} \right)}} & \;\end{matrix}$

where {right arrow over (d)}_(ix), {right arrow over (d)}_(ix), and{right arrow over (d)}_(ix) are the x, y, and z components in theparticular reference frame. When the antenna reference frame 430 isaligned with the mobile vehicle reference frame 420, the second unitvector {right arrow over (d)}′_(i) in the mobile vehicle reference frame420 will have the same x, y, and z, components as the corresponding unitvector in the antenna reference frame 430, and therefore the calculatedazimuth and elevation will be the same using either reference frame.However, when there is an antenna platform misalignment between themobile vehicle reference frame 420 and the antenna reference frame 430,directly using the second unit vector {right arrow over (d)}′_(i) todetermine an antenna azimuth and elevation, rather than thecorresponding unit vector in the antenna reference frame 430, willresult in the beam 155 of the antenna system 150-d not being pointeddirectly at the target satellite 110-d (e.g., due to antenna pointingerror associated with the antenna platform offset).

The pointing error can be identified by peaking the antenna system 150-dduring an alignment calibration procedure (e.g., as directed by analignment calibration controller 275), and reading the resulting azimuthand elevation directly from an antenna positioning motor or a sensor onthe antenna system 150-d, for example. However, correcting the error inthis manner is only valid for that particular orientation (e.g., azimuthdirection of the beam 155 or heading of the mobile vehicle 102-d). Inorder to provide a more general solution that will be valid in allorientations, the methods and apparatus according to the presentdisclosure may providing a best fit rotation matrix between the mobilevehicle reference frame 420 and the antenna reference frame 430 whilesimultaneously supporting the communication of user data during a travelsegment of the mobile vehicle 102-a.

In accordance with one embodiment of the disclosure, the antenna system150-d is peaked during user data communications of a travel segment todetermine the azimuth and elevation directions of the antenna system150-d that results in the maximum signal strength being communicated ina signal between the target satellite 110-d and the antenna system150-d. Signal strength can be determined based on the amplitude, signalto noise ratio (SNR), amount of received power, or other such metricrelated to the user data communication, which may include forward linkuser data or return link user data. In various examples the azimuth andelevation may be determined by control signals provided to a positioner153 (e.g., a positioning mechanism or a beamformer), read directly froma positioner 153, or read from a positioner sensor of the antenna system150-d.

In accordance with one embodiment of the disclosed method and apparatus,a step track technique is used (e.g., by an alignment calibrationcontroller) as an alignment calibration procedure to “peak” the antenna.In one such step track peaking procedure, the antenna system 150-apoints a beam 155 toward the target satellite 110-d using an estimatedpointing direction, identified in antenna elevation and azimuth, that isbased at least in part on positional information of the mobile vehicle102-d (e.g., a location of the mobile vehicle 102-d, and an attitude ofthe mobile vehicle 102-d). In some examples, the offset between themobile vehicle reference frame 420 and the antenna reference frame 430will not be so great that the signal communicated via the beam 155 isnot detectable. Therefore, in accordance with one embodiment, theantenna azimuth and elevation calculated under the assumption that thereis no offset between the mobile vehicle reference frame 420 and theantenna reference frame 430 is a sufficiently accurate estimate at whichto begin the peaking procedure.

In examples where calibration is performed on signals received at theantenna system 150-d, a measurement of a signal characteristic of theuser data received through the antenna system 150-d may be performed.The orientation of the beam 155 may subsequently be changed in elevationand/or azimuth by one “step” by the ACU 270 (e.g., as directed by thealignment calibration controller 275) providing an associated command toa positioner 153 (e.g., a pointing mechanism and/or a beamformer). Insome examples the alignment calibration controller 275 may direct theantenna system 150-a to implement the peaking technique based onreceived power measurements provided from a modem 230. Additionally oralternatively, the received power may be measured by a device other thana modem, that is located elsewhere along the receive chain can be usedto measure the received power.

For example, if the level of received power drops after changing theelevation of the beam 155, the antenna system 150-d may move the beam inthe opposite elevation direction. In one embodiment, the antenna system150-d moves the orientation of the beam 155 by two steps. If the amountof received power increases, the beam 155 is moved another step furtherin that direction. Another power measurement is made. Each time theamount of receive power increases, the beam 155 is moved another “step”in the same direction that results in the greater signal strength beingreceived in a signal from the target satellite 110-d. Upon measuring adrop in the received power, the direction of the beam 155 may be movedone step back. Once the peak power measurement for elevation has beendetected, the antenna may begin a similar search for the peak signalcharacteristic in the azimuth direction. If the initial azimuthdirection was not associated with the peak received power measured fromthe user data, then the search in the elevation direction may berepeated. If the antenna was not at the elevation associated with thepeak received power, then the search in the azimuth direction may againrepeated. This process may continue until a direction for the peakreceived power is determined in both the elevation and the azimuthdirections.

Although the described step track procedure is one example of analignment calibration procedure that may support dynamic antennaplatform offset calibration, many modifications to this procedure can beimplemented to improve the likelihood that the beam 155 is at the bestpointing elevation and azimuth. Furthermore, other peaking techniquescan be employed to provide an alignment calibration procedure, such as,but not limited to, techniques known commonly as conical scan (conscan)or sine scan.

In addition to determining the azimuth and elevation of the beam 155associated with the peak signal characteristic, the alignmentcalibration controller 275 may associate the alignment calibrationprocedure with a spatial condition. In one example, the alignmentcalibration controller 275 may associate the calibration procedure withan azimuth direction of the beam 155 (e.g., as an average azimuthdirection over the alignment calibration procedure, or an azimuthdirection at an initial, middle, or final time of the alignmentcalibration procedure). In another example, the alignment calibrationcontroller 275 may associate the calibration procedure with a headingdirection of the mobile vehicle 102-d (e.g., as an average headingdirection over the alignment calibration procedure, or a headingdirection at an initial, middle, or final time of the alignmentcalibration procedure). In various examples, the spatial conditionassociated with an alignment calibration procedure may include any oneor more of azimuth of the beam 155, elevation of the beam 155, yaw ofthe mobile vehicle 102-d, pitch of the mobile vehicle 102-d, roll of themobile vehicle 102-d, or other indications of spatial alignment betweenthe mobile vehicle 102-d and the target satellite 110-d, or otherindications spatial orientation of the antenna system 150-d (e.g.,positioner alignment directions). Results from the alignment calibrationprocedure (e.g., a calibration vector set) may later be used todetermine an antenna platform offset.

As previously discussed, a single calibration vector set may not besuitable for determining an antenna platform offset. Further, a clusterof calibration vector sets with little spatial separation leads to apoor solution (e.g., a poorly conditioned matrix where small errors inthe measurement lead to larger errors in the solution). Thus, inaccordance with aspects of the present disclosure, the alignmentcalibration controller 275 may continue to perform alignment calibrationprocedures during the communication of user data until determining thatthe alignment calibration procedure has been performed for a pluralityof spatial conditions that satisfy a spatial separation criteria.

For example, when the spatial condition associated with the alignmentcalibration procedures comprises an azimuth direction of the beam 155,the 360 degrees of azimuth range may be divided into eight “bins” eachcovering a different 45-degree range of azimuth. In one example, thealignment calibration procedures may be repeated by the alignmentcalibration controller 275 until a calibration vector set is obtainedfor an azimuth direction in each of the bins. In another example, thealignment calibration procedures may be repeated by the alignmentcalibration controller 275 until there are no longer two adjacent binsthat are not associated with an alignment calibration procedure (e.g.,having completed an alignment calibration procedure for at least everyother bin). In another example, the alignment calibration procedures maybe repeated by the alignment calibration controller 275 until themaximum angular separation between adjacent azimuth directionsassociated with a completed alignment calibration procedure is below athreshold angle (e.g., 45 degrees, or some other angle, between azimuthdirections associated with a respective alignment calibrationprocedure).

A calibration vector set may be associated with each of the alignmentcalibration procedures performed at the plurality of spatial conditions.In various examples the calibration vector sets may each be determinedupon the completion of a respective alignment calibration procedure, orthe calibration vector sets may be calculated upon determining that thealignment calibration procedure has been performed for the plurality ofspatial conditions that satisfy the spatial separation criteria. Thecalibration vector sets may each include vector information to be usedin calculating the antenna platform offset between the antenna system150-d (e.g., antenna reference frame 430) and the IRU 280-c (e.g.,mobile vehicle reference frame 420), which may be an approximation ofthe antenna platform offset between the antenna system 150-d and the IRU280-c.

In one example each calibration vector set may include an estimatedpointing direction from the antenna to the target satellite that isdetermined based at least in part on positional information of themobile vehicle (e.g., the theoretical direction to the target satellite110-d, which may be based on previously-determined offsets), and alsothe peaked pointing direction from the antenna to the target satellitethat is determined during the respective alignment calibrationprocedure.

In some examples the estimated pointing direction and the peakedpointing direction (e.g., of a calibration vector set) may each beidentified in antenna azimuth and antenna elevation directions. Theazimuth and elevation at each spatial condition may each be converted toa respective third unit vector {right arrow over (d)}″_(i) in theantenna reference frame 430 using the following relationship, where a isantenna azimuth and E is antenna elevation:

{right arrow over (d)}″ _(ix)=cos ϵ_(i) cos α_(i)

{right arrow over (d)}″ _(iy)=cos ϵ_(i) sin α_(i)

{right arrow over (d)}″ _(iz)=−sin ϵ_(i)  (4)

Accordingly, for each spatial condition, there may be a first unitvector {right arrow over (d)} representing the estimate of the pointingdirection determined by the location of the antenna system 150 and thelocation of the satellite 106, in coordinates defined with respect tothe global reference frame 410 (e.g., the topocentric NED referenceframe). In addition, there may be a second unit vector {right arrow over(d)}′_(i) representing the estimate of the pointing direction incoordinates defined with respect to the mobile vehicle reference frame420 (e.g., a reference frame of the IRU 280-c) and a third vector {rightarrow over (d)}″_(i) representing the peaked pointing direction incoordinates defined with respect to the antenna reference frame 430. Thecollection of second unit vectors {right arrow over (d)}′_(i) in themobile vehicle reference frame 420 forms a first matrix D′, which mayhave dimensions of M rows and N columns, where M is the number of secondunit vectors and N is the number of axes of the mobile vehicle referenceframe 420 (e.g., three, with the columns representing the x′, y′, and z′components, respectively). The collection of third unit vectors {rightarrow over (d)}″_(i) in the antenna reference frame 430 forms a secondmatrix D″, which may also have dimensions of M rows and N columns, whereM is the number of third unit vectors (e.g., equal to the number ofsecond unit vectors) and N is the number of axes of the antennareference frame 430 (e.g., also three, representing the x″, y″, and z″components, respectively). If each collection of second and thirdvectors has no measurement noise or other source of error orinconsistency, then the first matrix is related to the second by thefollowing equation, where T is a rotation matrix:

D″=TD′  (5)

Once a sufficient number of measurements for {right arrow over (d)}′_(i)and {right arrow over (d)}″_(i) have been gathered (e.g., measurementsat the plurality of spatial conditions that satisfy the spatialseparation criteria), the rotation matrix T can be solved. By solvingfor T, the general transformation from the mobile vehicle referenceframe 420 to the antenna reference frame 430 can be calculated (e.g.,the antenna platform offset in each of the three axes, roll, pitch andyaw can be determined and used to calculate an alias transformation).Subsequently, the output of the IRU 280-c can be transformed by thealias transformation (e.g., the antenna platform offset) prior to beingused to calculate the azimuth and elevation needed to point the beam 155to the target satellite 110-d.

In some examples, solving for T in Eq. 5 may include using thepseudoinverse of the collection of vectors in the mobile vehiclereference frame 420. One example is to use singular value decomposition(SVD) to determine the pseudoinverse of the collection of vectors D′ inthe mobile vehicle reference frame 420 (where the notation B⁺ representsthe pseudoinverse of B). By multiplying each side of equation Eq. 5 bythe pseudoinverse D′⁺ of D′, the following equations result:

D″=TD′

D″D ⁺ =TD′D′ ⁺

T=D″D′ ⁺  (6)

The pseudoinverse can be calculated by using the elements of the SVD ofD′:

D′=USV*

D′ ⁺ =VS ⁺ U ^(*)  (7)

where U is a real or complex unitary matrix, S is a rectangular diagonalmatrix with non-negative real numbers on the diagonal, and V is a realor complex unitary matrix

The elements of Eq. 7 may be solved according to various linear algebramethods. For example, the pseudoinverse of S may be computed by takingthe transpose of the matrix formed with diagonal elements equal to thereciprocal of the diagonal elements of S. For a collection ofmeasurements that are noisy or that have other errors, use of thepseudoinverse will produce a least-squares estimate {circumflex over(T)} of the rotation T:

{circumflex over (T)}=D″D′ ⁺  (8)

where {circumflex over (T)} may be interpreted as the product of roll,pitch, and yaw rotations.

Although the SVD calculations described herein illustrate one examplefor solving for, or estimating the rotation matrix T that minimizes theerror between D″ and D′, other methods may be used, such as Procrustesanalysis. The elements of the rotation matrix T, or estimate thereof(e.g., the least squares estimate {circumflex over (T)} of thecomposition rotation matrix T), may be used to derive the roll, pitchand yaw offsets of the antenna reference frame 430 relative to themobile vehicle reference frame 420 (e.g., an antenna platform offsetcalibration between the vectors {right arrow over (d)}′_(i) and {rightarrow over (d)}″_(i)). For example, the composite rotation matrix T_(i)may be given as:

$\begin{matrix}{\mspace{79mu} {{T_{i}\left( {R_{0},P_{0},Y_{0}} \right)} = {\begin{bmatrix}r_{11} & r_{11} & r_{11} \\r_{11} & r_{11} & r_{11} \\r_{11} & r_{11} & r_{11}\end{bmatrix} = \left\lbrack {\begin{matrix}{{\cos \left( P_{0} \right)}*{\cos \left( Y_{0} \right)}} & {{\cos \left( P_{0} \right)}*{\sin \left( Y_{0} \right)}} & {- {\sin \left( P_{0} \right)}} \\{{{\sin \left( R_{0} \right)}*{\sin \left( P_{0} \right)}*{\cos \left( Y_{0} \right)}} -} & {{{\sin \left( R_{0} \right)}*{\sin \left( P_{0} \right)}*{\sin \left( Y_{0} \right)}} +} & {{\sin \left( R_{0} \right)}*{\cos \left( P_{0} \right)}} \\{{\cos \left( R_{0} \right)}*{\sin \left( Y_{0} \right)}} & {{\cos \left( R_{0} \right)}*{\cos \left( Y_{0} \right)}} & \; \\{{{\cos \left( R_{0} \right)}*{\sin \left( P_{0} \right)}*{\cos \left( Y_{0} \right)}} +} & {{{\cos \left( R_{0} \right)}*{\sin \left( P_{0} \right)}*{\sin \left( Y_{0} \right)}} -} & {{\cos \left( R_{0} \right)}*{\cos \left( P_{0} \right)}} \\{{\sin \left( R_{0} \right)}*{\sin \left( Y_{0} \right)}} & {{\sin \left( R_{0} \right)}*{\cos \left( Y_{0} \right)}} & \;\end{matrix}\text{?}} \right.}}} & (9) \\{\text{?}\text{indicates text missing or illegible when filed}} & \;\end{matrix}$

Accordingly, from Eq. 9, the solutions to the roll, pitch and yawrotation may be determined as follows:

Y ₀=tan⁻¹(r ₁₂ /r ₁₁)

P ₀=tan⁻¹(−r ₁₃/√{square root over (r ₂₃ ² +r ₃₃ ²))}

R ₀=tan⁻¹(r ₂₃ /r ₃₃)  (10)

Thus, a vector represented in the mobile vehicle reference frame 420(e.g., a vector derived in the global reference frame 410 and translatedto the mobile vehicle reference frame 420, or a vector identified in themobile vehicle reference frame 420, such as an output of the IRU 280-c)can subsequently be transformed by an alias transform to the antennareference frame 430 using knowledge of the roll, pitch, and yawrotations (e.g., the antenna platform offset) determined by Eq. 10. Inaccordance with aspects of the present disclosure, this knowledge of theroll, pitch, and yaw rotations may therefore be applied to the output ofthe IRU 280-c to compensate for antenna platform misalignment betweenthe antenna system 150-d and the IRU 280-c, and an azimuth and elevationcan be calculated based on the compensated IRU data (e.g., by applyingEq. 3 to the components of a unit vector {right arrow over (d)}″_(i)aligned with a pointing direction in the antenna reference frame 430).

FIG. 5 illustrates an example of a method 500 for dynamic antennaplatform offset calibration in accordance with aspects of the presentdisclosure. The operations of the method 500 are described withreference to an antenna system 150, including an alignment calibrationcontroller 275, an ACU 270, a positioner 153 (e.g., a pointing mechanismand/or a beamformer), and an antenna 152 associated with a beam 155,which may be examples of the corresponding components described withreference to FIGS. 1 through 4. The operations may be performedaccording to a global reference frame 410, a mobile vehicle referenceframe 420, and an antenna reference frame 430, as described withreference to FIG. 4. The antenna system 150 may be mounted on a mobilevehicle 102 to support communications with a target satellite 110, whichmay be examples of a mobile vehicle 102 or a target satellite 110described with reference to FIGS. 1 through 4. Although method 500 isdescribed with reference to a single target satellite 110, variouscommunications and dynamic antenna platform offset calibrationoperations may be performed with more than one target satellite 110,including those operations described below with reference to one or moretarget satellites 110.

In the example of method 500, the spatial condition associated with analignment calibration procedure is the beam azimuth direction (e.g.,identified with reference to the antenna reference frame 430). Forexample, an alignment calibration procedure (e.g., a step track cycle)may be associated with a particular azimuth direction, which may becalculated as an average or weighted average of azimuth over theduration of the alignment calibration procedure, or an initial, middle,or final azimuth angle during the alignment calibration procedure.Accordingly, when a step track cycle associated with a particularazimuth angle is performed (e.g., when a step track cycle is performedwhile the antenna is pointed in a particular azimuth direction or rangeof directions), the associated calibration vector set may provide a steptrack solution for the azimuth bin that includes the particular azimuthangle. Although the method 500 is described with reference to azimuthangle, in other examples spatial conditions may include one or moreother characteristics (e.g., beam azimuth, beam elevation, mobilevehicle yaw, mobile vehicle pitch, mobile vehicle roll, relativeposition between the mobile vehicle 102 and the target satellite 110, orany combination thereof).

Further, in the example of method 500, the spatial separation criteriaassociated with performing an antenna platform offset calibration is thefilling of azimuth “bins,” where each bin represents a different45-degree range of beam azimuth direction, and a total of 8 bins areassociated with the entire range of 360 degrees of beam azimuth. In theexample of method 500, an antenna platform offset is determined uponperforming an alignment calibration procedure for azimuth directions ineach of the eight bins. Although filling each of the spatial bins thatdefine a range is used to illustrate satisfying a spatial separationcriteria in the example of method 500, different spatial separationcriteria may be used, such as filling a different distribution of bins(e.g., every other bin, or filling bins until there are no longer twoadjacent bins that have not been filled), or performing an alignmentcalibration procedure for a set of spatial conditions having no greaterthan a threshold amount of separation (e.g., a set of beam azimuthdirections where a largest separation between adjacent directions is nogreater than 45 degrees).

At 505 the method 500 may include determining a calibration status ofthe antenna system 150. For example, at 505 the alignment calibrationcontroller 275 may determine that a prior antenna platform offsetcalibration procedure has not been performed, which may includedetermining that the antenna system 150 is operating with no priorcalibration (e.g., a ‘zero’ antenna alignment platform offset) or amanual antenna alignment platform offset calibration (e.g., amanually-entered calibration such as a physically measured antennaalignment offset or a statistical average antenna alignment offset, orsome other default calibration). If the alignment calibration controller275 determines at 505 that a prior antenna platform offset calibrationprocedure has not been performed, which may be associated withcommunication operations according to a first tracking mode as describedherein, the alignment calibration controller 275 may set the calibrationstatus to “calibrating” and proceed to 510. In other examples thealignment calibration controller 275 may determine that a prior antennaplatform offset calibration procedure has been performed, which mayinclude determining that the antenna system 150 is operating with apreviously determined antenna platform offset calibration. If thealignment calibration controller 275 determines at 505 that a priorantenna platform offset calibration procedure has been performed, whichmay be associated with communication operations according to a secondtracking mode, the alignment calibration controller 275 may set thecalibration status to “calibrated” and proceed to 511.

At 510, the method 500 may include the alignment calibration controller275 waiting for a first amount of time prior to proceeding withoperations associated with determining an antenna platform offsetcalibration. According to the example of method 500, the wait time maybe zero, in which case the method 500 proceeds directly from 505 to 515.In other examples the method 500 may include the alignment calibrationcontroller 275 waiting for a relatively short amount of time (e.g., incomparison with the wait time of 511). Thus, according to the wait timeof 510, the subsequent calibration operations may be directed by thealignment calibration controller 275 according to a first periodicinterval (e.g., a first periodicity). In the case where the wait time of510 is zero, the subsequent calibration operations may be performedcontinuously. While waiting at 510, the antenna system 150 may supportuser data communications by pointing the beam 155 of the antenna 152towards the target satellite 110 at the estimated aligned direction(e.g., as determined by positional information of the mobile vehicle102, without a sweeping of the beam 155 to misaligned directionsassociated with an alignment calibration procedure).

With the relatively short wait time of 510, an antenna platform offsetmay be determined relatively quickly (e.g., for determining an initialantenna platform offset while operating according to a first trackingmode). Further, the relatively short wait time of 510 may also supportmore frequent step track cycles that refine pointing of the beam 155 inthe absence of an antenna platform offset calibration, or with arelatively coarse antenna platform offset calibration. However, in someexamples (e.g., while operating according to a first tracking mode) userdata communications may be somewhat degraded due to relatively frequentpointing of the beam 155 in misaligned directions, which may beassociated with communicating relatively frequently with a lower gain ofthe antenna 152. For example, the relatively lower gain of the antenna152 in the misaligned directions may be compensated for by using arelatively lower MCS for user data communications, which may beassociated with a reduction of the data rate of user datacommunications.

At 511, the method 500 may include the alignment calibration controller275 waiting for a second amount of time prior to proceeding withprocedures associated with determining an antenna platform offset.According to the example of method 500, the wait time may be “normal”,which may be a period of time measured in second, minutes, hours, clockcycles, computational cycles, or others. In other words, at 511 themethod 500 may include the alignment calibration controller 275 waitingfor a relatively long amount of time (e.g., in comparison with the waittime of 510). Thus, according to the wait time of 511, the subsequentalignment calibration procedure may be directed by the alignmentcalibration controller 275 according to a second periodic interval(e.g., a second periodicity). According to one example, the “normal”wait time may be 10 minutes, such that alignment calibration proceduresmay be performed every 10 minutes. While waiting at 511, the antennasystem 150 may support user data communications by pointing the beam 155of the antenna 152 towards the target satellite 110 at the estimatedaligned direction (e.g., as determined by positional information of themobile vehicle 102, without a sweeping of the beam 155 to misaligneddirections associated with an alignment calibration procedure).

With the relatively longer wait time of 511, an antenna platform offsetmay be determined relatively slowly (e.g., for determining ongoingrefinement to an antenna platform offset while operating according to asecond tracking mode). However, in some examples (e.g., while operatingaccording to a second tracking mode) user data communications may besomewhat improved due to relatively infrequent pointing of the beam 155in misaligned directions. In other words, communicating according to asecond tracking mode associated with the longer wait time of 511 may beassociated with more frequent communications having a relatively highergain of the antenna 152, which may support relatively higher data ratesby way of a relatively higher modulation and coding rate.

Although illustrated with two different wait times, antenna platformoffset calibration procedures in accordance with the present disclosuremay have more than two wait times following the operations of 505. Forexample, a wait time between 505 and 515 may be calculated by thealignment calibration controller 275 based on various factors includingan operating mode, a calculated quality of calibration(s), a user datacommunications rate (e.g., less frequent alignment calibrationprocedures when user data rate is relatively high, and more frequentalignment calibration procedures when user data rate is relatively low),or other factors. Thus, the operations of an antenna alignment offsetcalibration procedure in accordance with the present disclosure may beperformed by the alignment calibration controller 275 according tovarious periodic intervals.

At 515, the method 500 may include the alignment calibration controller275 performing a step track cycle during the communication of user datawith the target satellite 110 via the beam 155, which may be an exampleof performing an alignment calibration procedure in accordance withaspects of the present disclosure. The step track cycle described hereinmay include various examples of pointing the beam 155 at directionsdifferent from a nominal direction (e.g., misaligned directionsdifferent from an estimate of an aligned direction between the antenna152 and the target satellite 110), and determining whether a signalcharacteristic measured from the communication of user data is greaterto, or lesser than when the beam 155 is pointed in the nominaldirection. In some examples the step track cycle performed at 515 mayinclude scanning across a plurality of orientations of the beam 155, andmay occur over a period of approximately 30 to 60 seconds.

Accordingly, the step track cycle may identify a difference between anestimated direction of highest gain for the beam 155 of the antenna 152(e.g., an estimate of an aligned direction between the antenna 152 andthe target satellite 110-e), and a peaked direction associated with thedirection of the beam 155 having a peak signal characteristic (e.g.,highest signal strength or highest SNR) as measured during user datacommunication with the target satellite 110. The estimated pointingdirection from the antenna 152 to the target satellite 110 may bedetermined based at least in part on positional information of themobile vehicle 102 (e.g., position and attitude as provided by an IRUand/or a GPS), and the peaked pointing direction from the antenna 152 tothe target satellite 110 may be determined based at least in part on ameasured signal characteristic of the user data communicated during thealignment calibration procedure of 515.

In some examples at 515, the method 500 may also include recording theangular velocity of the pointing of the beam 155 during the step trackcycle. For example, at 515 the angular velocity of the beam 155 in termsof azimuth rate and elevation rate may be recorded into memory (e.g.,associated with the alignment calibration controller 275) by calculatinga running summation of values (e.g., according to a sum of squaredvalues for azimuth and elevation such as sumVelSqAz+=AzCmdVel*AzCmdVeland sumVelSqEl+=ElCmdVel*sumVelSqEl, where “sumVelSq” refers to arunning summation of velocity squared, “CmdVel” refers to a velocitycommand for a particular data sample). At 515, the method 500 may alsoinclude recording (e.g., incrementing) the number of data samplesrecorded during the respective step track cycle, which may be used as adivisor of the running summation of values for calculating an RMS of theangular velocity of pointing the beam 155. Alternatively, the number ofdata samples may be otherwise predetermined, such as a determined numberof samples associated with a predetermined time to perform a step trackcycle.

The step track cycle may be performed with respect to the degrees offreedom of the positioner 153, which in the example of method 500includes an elevation degree of freedom and an azimuth degree offreedom. Accordingly, the step track cycle at 515 may be associated withan estimate of an aligned direction of the beam 155 with respect to beamelevation and azimuth (e.g., relative to the antenna reference frame430), and a peaked direction of the beam 155 with respect to beamelevation and azimuth as measured by or commanded to the positioner 153(e.g., relative to the antenna reference frame 430). In other examplesof dynamic antenna platform offset calibration, the degrees of freedomof a positioner 153 may be different from elevation and azimuth, and themethods described herein may be adjusted accordingly.

In examples where the antenna system 150 is operating with a “zero”antenna platform offset calibration, the estimate of the aligneddirection of the beam 155 may assume no antenna platform misalignment(e.g., assuming zero antenna platform offset in a calculation, oromitting the calculation that considers antenna platform offsetentirely). The peaked direction of the beam 155 may be different fromthe estimate of the aligned direction of the beam 155 due at least inpart to an antenna platform misalignment between the antenna 152 and asensor of the mobile vehicle 102. In examples where the estimated andpeaked pointing directions change over the course of the step trackcycle at 515 (e.g., due to movement of the target satellite 110-e,movement of the mobile vehicle 102-e, a change in attitude of the mobilevehicle 102-e, or a combination thereof), the estimated and peakedpointing directions may be averages, weighted averages, RMS, or someother statistical calculation of the pointing data associated with thestep track cycle at 515.

Although wait times of 510 and 511 are illustrated as being differentbetween the “calibrating” and “calibrated” states, other parameters mayalso be changed between the “calibrating” and “calibrated” steps. Forexample, operations of an alignment calibration procedure at 515 may beperformed differently based at least in part on the calibration state.Applying the calibration state at 515 may include determining a steptrack duration, step track azimuth and elevation increments, azimuth andelevation rates, and others, based at least in part on the currentcalibration state. In another example, an alignment calibrationprocedure may include conscan operations to determine an antennapointing offset, and the conscan operations may be performed relativelyquickly in the “calibrating” state and relatively slowly in the“calibrated” state.

At 520, the method 500 may include the alignment calibration controller275 determining whether the step track cycle has completed successfully.In various examples, the step track cycle at 515 may not have beencompleted successfully if the calculated antenna pointing offsets areexcessively high, if the estimate of the beamwidth is outside certainlimits, if the signal variation was too high, if a difference betweenantenna pointing offsets determined for multiple sub-procedures of thestep track cycle do not match closely enough, if the antenna lostcommunication with the satellite, if the step track cycle wasinterrupted, or if the satellite and/or the antenna went offline. If itis determined at 520 that the step track cycle has not completedsuccessfully, the method 500 may return to 505. If it is determined at520 that the step track cycle has completed successfully, the method 500may determine an antenna pointing offset for pointing the beam 155towards the target satellite 110 of the step track cycle at 515, or adifferent target satellite 110, for subsequent communication of firstuser data based at least in part on the positional information of themobile vehicle 102-e and the antenna pointing offset determined at 520,and the method 500 may proceed to 525. In other examples an alignmentcalibration procedure may not explicitly be “completed,” such as whenthe alignment calibration procedure is performed continuously. In suchexamples, at 520 the alignment calibration controller 275 mayalternatively determine that a suitable subset of calibration data hasbeen successfully acquired (e.g., upon determining that the criteriadescribed above are met, and according to a periodic collection ofvalues), and accordingly proceed to 525 upon such a determination whilethe alignment calibration procedure continues to be performed.

At 525, the method 500 may include alignment calibration controller 275determining whether the commanded azimuth (Az) and elevation (El)velocities of the step track cycle at 515 are below a velocity limit(e.g., a threshold angular rate). For example, when the commandedazimuth and elevation velocities are above the velocity limit, the beam155 may have been pointed at a wide range of orientations (e.g., due torelatively rapid change in attitude of the mobile vehicle 102), suchthat the data associated with the step track cycle at 515 may not besuitable for determining an antenna platform offset for the spatialcondition associated with the step track cycle. Also high velocity leadsto higher tracking error. In some examples, the tracking error (e.g.,servo error) or the standard deviation or variation in the azimuthand/or elevation directions may also be a criteria that determine thedata is not suitable to be used, in which case the alignment calibrationcontroller 275 may determine (e.g., at 525) whether the azimuth andelevation tracking error, standard deviation, or variation is below acorresponding threshold.

The velocity limit, tracking error, or axis position variationassociated with 525 may be common with the step track cycle operations(e.g., velocity limit, tracking error, or axis position variationassociated with a determination of a successful completion of a steptrack, as used in 520), or may be different velocity limit, trackingerror, or axis position variation associated particularly with assessingthe quality of alignment calibration procedure results for use indynamic antenna platform offset calibration. In the example of method500, the threshold velocity limit for both commanded azimuth angle andcommanded elevation angle may be 2.5 degrees per second. The commandedazimuth and elevation velocities of the step track cycle 515 may becalculated, for example, as an average velocity or an RMS velocity(e.g., according to an RMS calculation of RMSAzVel=sqrt(sumVelSqAz/numSamples), where sumVelSqAz and numSamples werecalculated during 515). If it is determined at 535 that the commandedazimuth and elevation velocities are not below the velocity limit, themethod 500 may return to 505 (e.g., without recording the results of thestep track procedure for the purpose of determining an antenna platformoffset). If it is determined at 535 that the commanded azimuth andelevation velocities are below the velocity limit, the method 500 mayproceed to 525.

At 530, the method 500 may include determining whether to store theresult of the alignment calibration procedure for the purpose ofdetermining an antenna platform offset. For example, at 530 thealignment calibration controller 275 may determine whether the azimuthbin associated with the step track cycle is empty, or if the currentstep track cycle is closer to a middle azimuth of the azimuth bin than aprior step track cycle. In the event that a bin is empty, the solutionfor the current step track cycle may fill the empty bin. In the eventthat a bin already has a step track cycle solution (e.g., a calibrationvector set for the bin), the solution for the current step track cyclemay replace a prior solution if the azimuth angle for the current steptrack cycle is closer to the middle azimuth angle of the associated bin,which may improve the spatial separation of the solution for the azimuthbin relative to the solution of adjacent azimuth bins. In anotherexample, the result of an alignment calibration procedure may be storedso long as space is available in memory associated with the alignmentcalibration controller 275 (e.g., space in storage location 541), and ifspace is not available in the memory, the result of the currentalignment calibration procedure may overwrite a previously saved resultwhen it improves the spatial separation of the stored results andotherwise discarded. Alternatively, the solution for the current steptrack cycle may be ignored for the purpose of determining an antennaplatform (e.g., deleted) if the azimuth angle for the current step trackcycle is farther from the middle azimuth angle of the associated bin.Whether the solution for the current step track cycle is stored or not,the solution for the current step track cycle (e.g., an antenna pointingoffset) may still be used for ongoing communications (e.g., until asubsequent antenna platform offset is determined).

Thus, a calibration vector set associated with a step track cycleanywhere in the azimuth bin may be accepted, but if a later solution isassociated with an azimuth direction closer to the center position ofthe bin, or some other measure of improved spatial distribution, it willoverwrite the earlier solution. This may support filling as many bins aspossible, while also spreading the results of alignment calibrationprocedures as much as possible (e.g., avoiding including too manyclosely-spaced results near a particular spatial condition, therebycausing the calculated antenna platform offset to be skewed by thosealignment calibration procedures performed near that particular spatialcondition), which may be accomplished without significantly slowing thecalibration process. Thus, if the azimuth bin is vacant, or if theazimuth direction associated with the step track cycle is close to thecenter of the azimuth bin, the method 500 may proceed to 535. Otherwise,the method 500 may return to 505 without recording the results of thestep track procedure for the purpose of determining an antenna platformoffset.

At 535, the method 500 may include storing the step track cyclesolution. The step track cycle solution may be stored in a storagelocation 541 associated with the azimuth bin. In some examples thestorage location 541 may be in non-volatile memory of the alignmentcalibration controller 275, so that solution is stored through powerdisruptions or through normal power cycles. This may, for example,permit the stitching together of step track solutions calculated overdifferent travel segments of the mobile vehicle 102-e (e.g., flights ofan aircraft), which may be beneficial because certain travel segmentsmay not include antenna pointing across a sufficient range of azimuthdirections.

In the example of method 500, the step track solution may include acalibration vector set including both the estimated aligned directionfrom the antenna 152-e to the target satellite 110-e, expressed in beamazimuth and elevation, and the peaked direction from the antenna 152-eto the target satellite 110-e, also expressed in beam azimuth andelevation. In other examples a calibration vector set may includedifferent representations of a step track solution, including anestimated aligned direction from the antenna 152-e to the targetsatellite 110-e and an antenna pointing offset, the peaked directionfrom the antenna 152-e to the target satellite 110-e and an antennapointing offset, simply the antenna pointing offset, or some othercalculated parameter of combination of parameters. Further, although thedescribed calibration vector set is described as having parameters intwo dimensions, other methods in accordance with the present disclosuremay have parameters in one dimension, or more than two dimensions.

Accordingly, in some examples, the method 500 may include performing acoordinate system transform at 540 prior to storing the step trackresults in storage location 541. For example, the step track solutionmay include an estimated aligned direction between the antenna 152 andthe target satellite 110. In some examples, this may be initiallycalculated by the alignment calibration controller 275 as aNorth-East-Down vector in a global coordinate system (e.g., globalreference frame 410 described with reference to FIG. 4). Accordingly,the estimated aligned direction may be transformed by the alignmentcalibration controller 275 into the mobile vehicle reference frame 420with Eq. 1 and Eq. 2 described above, using the attitude of the mobilevehicle 102 (e.g., pitch P_(i), roll R_(i), and yaw Y_(i), which may beprovided by an IRU 280 described with reference to FIG. 2). Further, insome examples, the estimated aligned direction may be transformed intothe antenna reference frame 430 with Eq. 1 and Eq. 2 described above,using a previously entered or calculated antenna platform offset (e.g.,pitch offset, roll offset, and yaw offset)

The representation of the unit vector for the estimated aligneddirection of the beam 155-e and/or the unit vector for the peakeddirection of the beam 155-e in the antenna reference frame 430-a mayrequire three variables (e.g., one for each of the X″-axis, Y″-axis, andZ″-axis) for each of the unit vectors. But in some examples, thecoordinate system transform at 540 may further convert therepresentation of unit vectors in the antenna reference frame 430 intotwo variables (e.g., elevation and azimuth directions, using Eq. 3),thereby reducing the number of variables stored in the storage location541 by one third.

At 545, the method 500 may include determining whether the spatialconditions associated with calibration vector sets satisfy a spatialseparation threshold. For example, at 545 the alignment calibrationcontroller 275 may determine whether enough azimuth bins are filled.Satisfying the spatial separation threshold may improve the results ofthe antenna platform offset calibration, such that the associatedmatrices are well-conditioned and invertible without excessive errors.For example, at 545 the antenna controller may determine whether a steptrack solution has been determined for each of eight 45-degree azimuthbins.

In other methods in accordance with the present disclosure, differentspatial separation thresholds may be applied at 545. For example, aspatial separation threshold may be satisfied when a calibration vectorset has been determined for a subset of azimuth bins such as at leastevery other azimuth bin (e.g., when there are no adjacent azimuth binsthat are not associated with a calibration vector set). Some examplesmay not use bins for satisfying a spatial separation criteria, andinstead may have a maximum separation between spatial conditionsassociated with calibration vector sets. For example, a spatialseparation threshold may be satisfied when a calibration vector set hasbeen determined for a plurality of beam azimuth directions where no twoadjacent beam azimuth directions are separated by more than 45 degrees.In such examples an antenna platform calibration offset may becalculated from vector calibration sets associated with as few as 8different azimuth directions, but may be calculated from vectorcalibration sets associated with more than 8 different azimuthdirections. Numerous other spatial separation thresholds may be usedprior to determining an antenna alignment offset calibration.

If it is determined that the spatial separation criteria are satisfied(e.g., enough azimuth bins are filled), the method 500 may proceed to550. Otherwise, the method 500 may return to 505 so that another steptrack cycle may be performed. Thus, the method 500 may include repeatingthe performance of an alignment calibration procedure (e.g., a steptrack cycle) until determining that the alignment calibration procedurehas been performed for a set of spatial conditions (e.g., beam azimuthdirections) that satisfy the spatial separation criteria (e.g., untilall of the azimuth bins are filled). In various examples the subsequentstep track cycles may be performed with the same target satellite 110,or with a different target satellite 110. In some cases a differenttarget satellite 110 having a different orbital position may be selectedin order to more rapidly fill different azimuth bins without requiringadditional orientations of the mobile vehicle 102. However the differenttarget satellites 110 may not support user data communication with theantenna system 150, so in some examples the same target satellite 110may be used for subsequent step track cycles in order to maintaincontinuity of user data service.

At 550, the method 500 may include computing an antenna platform offsetsolution. For example, using the calibration vector sets stored in theazimuth bins of storage location 541, the yaw, pitch, and roll offsetthat minimizes the square of the error may be computed by the alignmentcalibration controller 275 using a method such as the pseudo-inversesingle value decomposition technique described with reference to Eqs. 6through 10, Procrustes method, or any other method for determining aminimum error of a transform between matrices. In some examples this mayinclude converting the calibration vector sets from a representation inelevation and azimuth to a three-dimensional representation inrespective reference frames. For example, an estimated aligned directionof the beam 155-e for each azimuth bin may be converted into coordinatesin an X′ axis, a Y′ axis, and a Z′ axis of the mobile vehicle referenceframe 420-a (which may include a conversion using apreviously-calculated antenna platform offset), and the peaked directionof the beam 155-e for each azimuth bin may be converted into coordinatesin an X″ axis, a Y″ axis, and a Z″ axis of the antenna reference frame430-a. Each of the estimated aligned directions of the beam 155-e in themobile vehicle reference frame 420-a may represent a row of a firstmatrix (e.g., D′ of Eq. 6), and each of the peaked directions of thebeam 155-e in the antenna reference frame 430-a may represent a row of asecond matrix (e.g., D″ of Eq. 6). Accordingly, the antenna platformoffset may be calculated as the approximate transformation between thefirst matrix and the second matrix (e.g., calculating {circumflex over(T)} of Eq. 8, an approximation of T of Eq. 6, to arrive at roll, pitch,and yaw offsets according to Eq. 10).

At 555, the method 500 may include the alignment calibration controller275 determining whether a condition number of the antenna platformoffset calibration is below a threshold condition number, where thecondition number is the ratio of the largest versus the smallestnon-zero singular value calculated from a singular value decomposition(e.g., a Jacobian singular value decomposition), or calculated as thenorm of the matrix times the norm of the inverse of the matrix. Thecondition number may represent a measure of how “invertible” thesolution of the singular value decomposition is, where a relatively highcondition number may provide an indication that relatively small errorsin the input variables would lead to relatively large errors in theresults of the singular value decomposition. In one example, thethreshold condition number may be 2.0. If the condition number of theantenna platform offset calibration is less than the threshold conditionnumber, the method 500 may proceed to 560. If the condition number ofthe antenna platform offset calibration is not less than the thresholdcondition number, the method may return to 505 (which may includeclearing the step track solution of one or more azimuth bins).

At 560, the method 500 may include the alignment calibration controller275 determining whether residual values calculated with the antennaplatform offset solution are within predetermined error bounds, wherethe residual values at 560 refer to a difference between the peakeddirection of the beam 155-e and a newly estimated aligned direction ofthe beam 155-e that is determined based on the determined antennaplatform offset. For example, the determined yaw, pitch, and rolloffsets of the antenna platform offset may be used in a rotation matrixapplied to the previously-estimated aligned direction of the beam 155-e(e.g., when a “zero” antenna platform offset was used to determine thepreviously-estimated aligned direction of the beam 155-e). If thedifference between the newly estimated aligned direction of the beam155-e and the peaked direction of the beam 155-e is below thepredetermined error bounds for all of the azimuth bins, the results fromthe alignment calibration procedures performed at each of the spatialconditions may be suitable for calculating the antenna platform offset,and the method 500 may proceed to 580. Otherwise the method 500 mayproceed to 565. In one example of the method 500, the predeterminederror bounds may include an azimuth limit of ±0.3° and an elevationlimit of ±0.4°. In some examples the evaluations at 560 may includereference frame transformations such that these evaluations are madewith reference to the global reference frame 410-a, rather than theantenna reference frame 430-a.

If the difference between the newly estimated aligned direction of thebeam 155-e and the peaked direction of the beam 155-e is above thepredetermined error bounds for a particular azimuth bin, the results ofthe alignment calibration procedure for that azimuth bin may not besuitable for use in calculating an antenna platform offset. Thus, forthose azimuth bins that are associated with a difference between anewly-estimated direction of the beam 155-e and the peaked direction ofthe beam 155-e being above the predetermined error bounds, the bins maybe cleared at 565. Upon clearing such azimuth bins, the method 500 mayinclude incrementing an error counter stored in storage location 566(e.g., non-volatile memory of the ACU 270-c), and the method 500 mayproceed to 570. In some examples, if more than a threshold number ofbins are cleared (e.g., three or more azimuth bins) all of the azimuthbins may be cleared, and the method may return to 505.

In some examples, the method 500 may also include determining elevationand azimuth offsets for the antenna system 150 (e.g., at 560). Elevationand azimuth offsets may be used, for example, to compensate for issuessuch as encoder offset (e.g., a motor home position not being setcorrectly), encoder drift, physical misalignment between components,physical deflection of components, and other issues that cause adifference between a commanded or sensed orientation of the beam 155(e.g., as commanded to, or sensed by a positioner 153) and the actualorientation of the beam 155, as referenced to the antenna referenceframe 430, but are not a pure rotation in the global reference frame. Inaccordance with one embodiment of the disclosed method and apparatus, itis desirable to account for such elevation and azimuth errors as well.

The determination of elevation and/or azimuth offsets may use theresidual values calculated at 560 for determining whether the calculatedresidual values are within predetermined error bounds. For example, anelevation offset can be determined by taking the average difference inelevation between the peaked direction of the beam 155 for each steptrack solution and the newly determined estimated aligned direction ofthe beam 155 for the respective step track solution. Similarly, anazimuth offset can be determined by taking the average difference inazimuth between the peaked direction of the beam 155 for each step tracksolution and the newly determined estimated aligned direction of thebeam 155 for the respective step track solution. In some examples theazimuth error may be further adjusted by way of secant correction toconvert to a cross-elevation error, which may be associated with errorin aperture coordinates. The determined elevation and/or azimuth offsetsmay subsequently be used to improve tracking of the beam 155 (e.g., byapplying the determined elevation and/or azimuth offsets to commands ofelevation and/or azimuth provided to a positioner 153).

At 570, the method 500 may include the alignment calibration controller275 determining whether the error counter is greater than a thresholderror limit (e.g., greater than 8), which may indicate ongoingdifficulty in arriving at an antenna platform offset solution withwell-conditioned calibration vector sets. If the error counter is notdetermined to be greater than the threshold error limit, the method 500may proceed directly to 505 and perform another calibration cycle. Ifthe error counter is determined to be greater than the threshold errorlimit, the method 500 may proceed to 575.

At 575, the method 500 may include clearing all of the azimuth bins inorder to recalculate step track cycle solutions for each of the azimuthbins. At 575 the method 500 may also include clearing the error counter(e.g., resetting the error counter in storage location 566 to zero).Following the operations at 575 the method may proceed to 505 andperform another step track cycle.

At 580, the method 500 may include the alignment calibration controller275 determining an updated antenna platform offset calibration. In someexamples, such as when the antenna platform offset calculated at 550 isthe first calculated antenna platform offset, the updated antennaplatform offset of 580 may simply be equal to the antenna platformoffset calculated at 550. In other examples, to allow continuousimprovement, the antenna platform offset calculated at 550 may becombined with previously-calculated antenna platform offsets (e.g., byaveraging, weighted averaging, or other combination), which may beretrieved from storage location 581 (e.g., non-volatile memory of thealignment calibration controller 275).

In some examples, it may be preferable to average the rotations of theantenna platform offsets after first converting each antenna platformoffset to a quaternion, and averaging the quaternions. To convert theyaw, pitch, and roll offsets of an antenna platform offset to aquaternion rotation, the following equation may be used:

$\begin{matrix}{\begin{bmatrix}{qw} \\{qx} \\{qy} \\{qz}\end{bmatrix} = \begin{bmatrix}{{{\cos \left( \frac{roll}{2} \right)} \cdot {\cos \left( \frac{pitch}{2} \right)} \cdot {\cos \left( \frac{yaw}{2} \right)}} +} \\{{\sin \left( \frac{roll}{2} \right)} \cdot {\sin \left( \frac{pitch}{2} \right)} \cdot {\sin \left( \frac{yaw}{2} \right)}} \\{{{\sin \left( \frac{roll}{2} \right)} \cdot {\cos \left( \frac{pitch}{2} \right)} \cdot {\cos \left( \frac{yaw}{2} \right)}} -} \\{{\cos \left( \frac{roll}{2} \right)} \cdot {\sin \left( \frac{pitch}{2} \right)} \cdot {\sin \left( \frac{yaw}{2} \right)}} \\{{{\cos \left( \frac{roll}{2} \right)} \cdot {\sin \left( \frac{pitch}{2} \right)} \cdot {\cos \left( \frac{yaw}{2} \right)}} +} \\{{\sin \left( \frac{roll}{2} \right)} \cdot {\cos \left( \frac{pitch}{2} \right)} \cdot {\sin \left( \frac{yaw}{2} \right)}} \\{{{\cos \left( \frac{roll}{2} \right)} \cdot {\cos \left( \frac{pitch}{2} \right)} \cdot {\sin \left( \frac{yaw}{2} \right)}} -} \\{{\sin \left( \frac{roll}{2} \right)} \cdot {\sin \left( \frac{pitch}{2} \right)} \cdot {\cos \left( \frac{yaw}{2} \right)}}\end{bmatrix}} & (11)\end{matrix}$

Subsequently, each of the four components of the quaternion (qw, qx, qy,and qz) may be averaged individually, qw old with qw new, etc. Tosupport a weighted averaging, the number of successful calibrations isstored (e.g., in storage location 581) and is incremented by 1 afterthis successful calibration. After the antenna platform offsetcalculated at 550 is found to be acceptable, an example of instructionsfor performing a weighted quaternion averaging may include thefollowing:

Cal_counter++newWeight=1.0/Cal_counter

if newWeight<min_weight then newWeight=newWeightrotation=newRotation*newWeight+rotation*(1.0−newWeight)  (12)

where min_weight represents a minimum weighting to give the weightedaveraging some forgetfulness, such that if there is a physical change inantenna platform misalignment and the calibration is not otherwisereset, the weighted averaging is able to adapt more quickly. Otherwise,if the system had already recorded numerous calibrations, anunnecessarily large number of new antenna platform offset calibrationsmay be required to adapt to the physical change in antenna platformmisalignment.

After the quaternion has been averaged it may be converted to a unitvector (e.g., by dividing the quaternion elements by the magnitude ofthe quaternion) since such averaging may produce a quaternion that isnot quite a unit. The quaternions may be converted back to roll, pitch,and yaw offsets using the following equation:

$\begin{matrix}{\begin{bmatrix}{roll} \\{pitch} \\{yaw}\end{bmatrix}\begin{bmatrix}{\arctan \left( \frac{2\left( {{{qw} \cdot {qx}} + {{qy} \cdot {qz}}} \right)}{1 - {2\left( {{qx}^{2} + {qy}^{2}} \right)}} \right)} \\{\arcsin \left( {2\left( {{{qw} \cdot {qy}} - {{qz} \cdot {qx}}} \right)} \right)} \\{\arctan \left( \frac{2\left( {{{qw} \cdot {qz}} + {{qx} \cdot {qy}}} \right)}{1 - {2\left( {{qy}^{2} + {qz}^{2}} \right)}} \right)}\end{bmatrix}} & (13)\end{matrix}$

At 585, the method 500 may include the alignment calibration controller275 setting the calibration status to “calibrated,” (e.g., updating thestatus from “calibrating” to “calibrated,” or maintaining a status of“calibrated) which may result in a change in periodicity for subsequentalignment calibration procedures (e.g., as determined by a wait timesuch as wait times of 510 or 511). In some examples, updating thecalibration status to “calibrated” may cause alignment calibrationprocedures to be performed according to a longer periodicity, such thatreduction in signal strength or communications capacity associated withthe misaligned beam directions of the alignment calibration proceduresmay be reduced. At 585, the method 500 may also include the alignmentcalibration controller 275 clearing the azimuth bins and error count,such that another antenna alignment offset calibration may be computed(e.g., at 550) using new step track cycle solutions. Following theoperations of 585, the method 500 may return to 505 and begin anothercalibration cycle.

Various other operations that are not shown may also be included in themethod 500 to address particular circumstances. For example, to resetthe antenna platform offset calibration for reinstallation of an antennasystem, or portion thereof, all values of antenna platform offsetcalibrations and/or step track solutions may be deleted. In someexamples, this may include applying a “zero” antenna platform offsetcalibration, or trigger a request to enter a manual antenna platformoffset calibration. In various examples, resetting the antenna platformoffset calibration may be performed by an operator (e.g., executing areset command), or may be triggered based on a detected removal ordisconnection of the antenna system 150, a portion thereof, ordisconnection of some other component (e.g., disconnecting a wiringharness associated with the antenna system 150, or disconnecting awiring harness associated with an IRU of the mobile vehicle 102).

FIG. 6 shows a block diagram 600 of an example of an alignmentcalibration controller 275-a that supports dynamic antenna platformoffset calibration in accordance with aspects of the present disclosure.The alignment calibration controller 275-a may be an example of aspectsof the alignment calibration controllers 275 described with reference toFIGS. 1 through 5. In various examples, the alignment calibrationcontroller 275-a may be a stand-alone component of an antenna system150, may be integrated in another component of an antenna system 150(e.g., integrated in an ACU 270 and/or integrated in a modem 230), ormay be distributed across more than one component of an antenna system150. The alignment calibration controller 275-a may include an antennapointing manager 610, an alignment calibration procedure manager, and anantenna platform offset calibration manager 630. Each of thesecomponents may be in communication with one another (e.g., via one ormore signals or buses).

The components of the alignment calibration controller 275-a mayindividually or collectively be implemented using one or more ASICsadapted to perform some or all of the applicable functions in hardware.Alternatively, the functions may be performed by one or more otherprocessing units (or cores), on one or more integrated circuits. In someother examples, other types of integrated circuits may be used (e.g.,Structured/Platform ASICs, FPGAs, a SoC, and/or other types ofSemi-Custom ICs), which may be programmed in any manner known in theart. The functions of each component may also be implemented, in wholeor in part, with instructions embodied in a memory, formatted to beexecuted by one or more general or application-specific processors.

The antenna pointing manager 610 may manage aspects of pointing a beam155 (e.g., directing aspects of, or providing positioning information toan ACU 270). For example, the antenna pointing manager 610 may supportpointing the beam 155 of the antenna 152 towards a target satellite 110for communication of user data based at least in part on the positionalinformation of a mobile vehicle 102 and antenna pointing offset (e.g.,as determined by the alignment calibration procedure manager 620) in afirst tracking mode or a second tracking mode, as described herein. Insome examples, the antenna pointing manager 610 may further supportpointing the beam 155 of the antenna 152 towards a target satellite 110for communication of user data based at least in part on an antennaplatform offset (e.g., as determined by the antenna platform offsetcalibration manager 630) in a second tracking mode, as described herein.

The alignment calibration procedure manager 620 may manage variousaspects of performing an alignment calibration procedure. For example,the alignment calibration procedure manager may direct aspects ofperforming an alignment calibration procedure to determine an antennapointing offset based at least in part on a difference between anestimated pointing direction from the antenna 152 to the targetsatellite 110 that is determined based at least in part on positionalinformation of the mobile vehicle 102 and a peaked pointing directionfrom the antenna 152 to the target satellite 110 that is determinedbased at least in part on a measured signal characteristic of first userdata communicated during the alignment calibration procedure.

To support dynamic antenna platform offset calibration, the alignmentcalibration procedure manager 620 may direct alignment calibrationprocedures to the same target satellite 110, or a plurality of targetsatellites 110. Further, the alignment calibration procedure manager 620may direct alignment calibration procedures to include transmittingsignals from the antenna 152, receiving signals at the antenna 152, or acombination thereof. In some examples the alignment calibrationprocedure manager 620 may provide antenna pointing offsets associatedwith alignment calibration procedures to the antenna pointing manager610 to support pointing of the beam 155 along misaligned directions.

The antenna platform offset calibration manager 630 may manage variousaspects of determining an antenna platform offset. For example, theantenna platform offset calibration manager 630 may cause the alignmentcalibration procedure manager 620 to repeat performing the alignmentcalibration procedure until determining that the alignment calibrationprocedure has been performed for a plurality of spatial conditions thatsatisfy a spatial separation criteria. In one example, each of theplurality of spatial conditions includes an angular direction within oneof a plurality of angular ranges, and determining that the alignmentcalibration procedure has been performed for the plurality of spatialconditions that satisfy the spatial separation criteria includesdetermining that a number of angular ranges of antenna azimuth directionassociated with the plurality of spatial conditions satisfies athreshold number of angular ranges of antenna azimuth direction. Inanother example, determining that the alignment calibration procedurehas been performed for the plurality of spatial conditions that satisfythe spatial separation criteria may include determining that a maximumangular separation between adjacent pairs of the plurality of spatialconditions is less than or equal to a threshold angular separation.

In some examples the antenna platform offset calibration manager 630 maydetermine, for each of the calibration procedures performed for theplurality of spatial conditions, a respective calibration vector set(e.g., the estimated pointing direction from the antenna to the targetsatellite, the peaked pointing direction from the antenna to the targetsatellite, or both) based at least in part on the respective peakedpointing direction associated with the respective one of the pluralityof spatial conditions. In some examples, determining a respectivecalibration vector set is based at least in part on an angular rate ofpointing for the antenna being below a threshold angular rate, aresidual error being below a threshold residual error, a servo errorbeing below a servo error threshold, or a combination thereof.

In some examples, determining a respective calibration vector set isbased at least in part on identifying that a fitness metric associatedwith a new antenna calibration procedure taken at a new spatialcondition within one of the plurality of angular ranges associated witha previously determined calibration vector set exceeds the fitnessmetric associated with the previously determined calibration vector set,and replacing the previously determined calibration vector set with anew calibration vector set determined from the new antenna calibrationprocedure. For example, a fitness metric may include a relationship ofthe new spatial condition to a nominal direction of the one of theplurality of angular ranges, a quality metric associated with the newantenna calibration procedure, or a combination thereof.

After determining that the alignment calibration procedure has beenperformed for the plurality of spatial conditions that satisfy thespatial separation criteria, the antenna platform offset calibrationmanager 630 may determine an antenna platform offset between a referenceframe of the antenna and a reference frame of the mobile vehicle basedat least in part on the calibration vector sets determined for each ofthe calibration procedures performed for the plurality of spatialconditions.

In some examples, determining the antenna platform offset is based atleast in part on the antenna platform offset satisfying an offsetcalibration quality criteria, and the offset calibration qualitycriteria may include a calculated matrix condition number for theantenna platform offset being below a threshold matrix condition numberor residuals associated with the determined antenna platform offset foreach of the plurality of spatial conditions being below a threshold.

In some examples, the antenna platform offset calibration manager 630may determine that a residual based at least in part on the calculatedantenna platform offset is above a threshold residual for at least oneof a plurality of spatial conditions, and discard calibration vector setfor each of the at least one of the plurality of spatial conditions. Theantenna platform offset calibration manager 630 may subsequentlydetermining a new calibration vector set for each of the at least one ofthe plurality of spatial conditions.

In some examples, the antenna platform offset calibration manager 630may determine an updated antenna platform offset, which may be aninitial antenna platform offset (e.g., replacing a “zero” or manualcalibration), or may be a refined antenna platform offset based at leastin part on one or more previously-calculated antenna platform offsets.For example, the antenna platform offset calibration manager 630 maycalculate a weighted average of a plurality of calculated antennaplatform offsets.

FIG. 7 illustrates a block diagram 700 of an apparatus 705 that supportsdynamic antenna platform offset calibration in accordance with aspectsof the present disclosure. The apparatus 705 includes a processor 710,memory 715, an alignment calibration controller 275-b, and acommunications interface 740. Each of these components may be incommunication with each other, directly or indirectly, over one or morebuses 735. In various examples, the apparatus 705 may be, or be part ofan antenna system 150 described with reference to FIGS. 1 through 5.

The memory 715 may include random access memory (RAM) and/or read-onlymemory (ROM). The memory 715 may store an operating system (OS) 720(e.g., built on a Linux or Windows kernel). The memory 715 may alsostore computer-readable, computer-executable code 725 includinginstructions that are configured to, when executed, cause the processor710 to perform various functions described herein related dynamicantenna platform offset calibration. Alternatively, the code 725 may notbe directly executable by the processor 710 but be configured to causethe apparatus 705 (e.g., when compiled and executed) to perform one ormore of the functions described herein. In some examples, the memory 715may also include storage locations associated with the alignmentcalibration controller 275-b for various operations described herein(e.g., storage locations 541, 577, and 581 described with reference toFIG. 5). The communications interface 740 may transmit signals orreceive signals communicated with other components of the antenna system150.

The alignment calibration controller 275-b may be an example of thealignment calibration controllers 275 described with reference to FIGS.1 through 6. The apparatus 705, including the alignment calibrationcontroller 275-b, may manage one or more aspects of dynamic antennaplatform offset calibration, as described herein. In some examples thealignment calibration controller 275-b may support an antenna system 150communicating, at a mobile vehicle 102 according to a first trackingmode during one or more travel segments of the mobile vehicle 102, firstuser data with a target satellite 110 via a beam 155 of an antenna 152mounted to the mobile vehicle 102. As directed by the alignmentcalibration controller 275-b, communicating the first user dataaccording to the first tracking mode may include performing an alignmentcalibration procedure to determine an antenna pointing offset based atleast in part on a difference between an estimated pointing directionfrom the antenna 152 to the target satellite 110 that is determinedbased at least in part on positional information of the mobile vehicle102, and a peaked pointing direction from the antenna 152 to the targetsatellite 110 that is determined based at least in part on a measuredsignal characteristic of the first user data communicated during thealignment calibration procedure. The alignment calibration controller275-b may subsequently direct (e.g., via a command or updated antennapositioning offsets provided to an ACU 270) pointing the beam 155 of theantenna 152 towards the target satellite 110 for subsequentcommunication of the first user data based at least in part on thepositional information of the mobile vehicle 102 and the determinedantenna pointing offset.

In accordance with the methods described herein, the alignmentcalibration controller 275-b may repeat the alignment calibrationprocedure until determining that the alignment calibration procedure hasbeen performed for a plurality of spatial conditions that satisfy aspatial separation criteria. The alignment calibration controller 275-bmay subsequently determine, for each of the calibration proceduresperformed for the plurality of spatial conditions, a respectivecalibration vector set based at least in part on the respective peakedpointing direction associated with the respective one of the pluralityof spatial conditions. Based at least in part on determining that thealignment calibration procedure has been performed for the plurality ofspatial conditions that satisfy the spatial separation criteria, thealignment calibration controller 275-b may determine an antenna platformoffset between a reference frame of the antenna 152 (e.g., an antennareference frame 430) and a reference frame of the mobile vehicle 102(e.g., a mobile vehicle reference frame 420) based at least in part onthe calibration vector sets determined for each of the alignmentcalibration procedures performed for the plurality of spatialconditions.

Subsequent to determining of the antenna platform offset, the alignmentcalibration controller 275-b may direct communication of second userdata with the target satellite 110 via the beam 155 of the antenna 152according to a second tracking mode, wherein communicating the seconduser data according to the second tracking mode includes pointing thebeam 155 of the antenna 152 towards the target satellite 110 forcommunicating the second user data based at least in part on thepositional information of the mobile vehicle 102 and the determinedantenna platform offset (e.g., as provided to an ACU 270).

The apparatus 705, including the processor 710, the memory 715, thealignment calibration controller 275-b and/or the communicationsinterface 740 may be implemented or performed with a general-purposeprocessor, a digital signal processor (DSP), an ASIC, an FPGA or otherprogrammable logic device, discrete gate or transistor logic, discretehardware components, or any combination thereof designed to perform thefunctions described herein. A general-purpose processor may be amicroprocessor, but in the alternative, the processor may be anyconventional processor, controller, microcontroller, or state machine.The apparatus 705 may also be implemented as a combination of computingdevices, e.g., a combination of a DSP and a microprocessor, multiplemicroprocessors, one or more microprocessors in conjunction with a DSPcore, integrated memory, discrete memory, or any other suchconfiguration

The detailed description set forth above in connection with the appendeddrawings describes examples and does not represent the only examplesthat may be implemented or that are within the scope of the claims. Theterm “example,” when used in this description, mean “serving as anexample, instance, or illustration,” and not “preferred” or“advantageous over other examples.” The detailed description includesspecific details for the purpose of providing an understanding of thedescribed techniques. These techniques, however, may be practicedwithout these specific details. In some instances, well-known structuresand apparatuses are shown in block diagram form in order to avoidobscuring the concepts of the described examples.

Information and signals may be represented using any of a variety ofdifferent technologies and techniques. For example, data, instructions,commands, information, signals, bits, symbols, and chips that may bereferenced throughout the above description may be represented byvoltages, currents, electromagnetic waves, magnetic fields or particles,optical fields or particles, or any combination thereof.

The various illustrative blocks and components described in connectionwith the disclosure herein may be implemented or performed with ageneral-purpose processor, a digital signal processor (DSP), an ASIC, anFPGA or other programmable logic device, discrete gate or transistorlogic, discrete hardware components, or any combination thereof designedto perform the functions described herein. A general-purpose processormay be a microprocessor, but in the alternative, the processor may beany conventional processor, controller, microcontroller, or statemachine. A processor may also be implemented as a combination ofcomputing devices, e.g., a combination of a DSP and a microprocessor,multiple microprocessors, microprocessors in conjunction with a DSPcore, or any other such configuration.

The functions described herein may be implemented in hardware, softwareexecuted by a processor, firmware, or any combination thereof. Ifimplemented in software executed by a processor, the functions may bestored on or transmitted over as instructions or code on acomputer-readable medium. Other examples and implementations are withinthe scope of the disclosure and appended claims. For example, due to thenature of software, functions described above can be implemented usingsoftware executed by a processor, hardware, firmware, hardwiring, orcombinations of any of these. Features implementing functions may alsobe physically located at various positions, including being distributedsuch that portions of functions are implemented at different physicalpositions. As used herein, including in the claims, the term “and/or,”when used in a list of two or more items, means that any one of thelisted items can be employed by itself, or any combination of two ormore of the listed items can be employed. For example, if a compositionis described as containing components A, B, and/or C, the compositioncan contain A alone; B alone; C alone; A and B in combination; A and Cin combination; B and C in combination; or A, B, and C in combination.Also, as used herein, including in the claims, “or” as used in a list ofitems (for example, a list of items prefaced by a phrase such as “atleast one of” or “one or more of”) indicates a disjunctive list suchthat, for example, a list of “at least one of A, B, or C” means A or Bor C or AB or AC or BC or ABC (i.e., A and B and C).

Computer-readable media includes both computer storage media andcommunication media including any medium that facilitates transfer of acomputer program from one place to another. A storage medium may be anyavailable medium that can be accessed by a general purpose or specialpurpose computer. By way of example, and not limitation,computer-readable media can comprise RAM, ROM, EEPROM, flash memory,CD-ROM or other optical disk storage, magnetic disk storage or othermagnetic storage devices, or any other medium that can be used to carryor store desired program code means in the form of instructions or datastructures and that can be accessed by a general-purpose orspecial-purpose computer, or a general-purpose or special-purposeprocessor. Also, any connection is properly termed a computer-readablemedium. For example, if the software is transmitted from a website,server, or other remote source using a coaxial cable, fiber optic cable,twisted pair, digital subscriber line (DSL), or wireless technologiessuch as infrared, radio, and microwave, then the coaxial cable, fiberoptic cable, twisted pair, DSL, or wireless technologies such asinfrared, radio, and microwave are included in the definition of medium.Disk and disc, as used herein, include compact disc (CD), laser disc,optical disc, digital versatile disc (DVD), floppy disk and Blu-ray discwhere disks usually reproduce data magnetically, while discs reproducedata optically with lasers. Combinations of the above are also includedwithin the scope of computer-readable media.

As used herein, the phrase “based on” shall not be construed as areference to a closed set of conditions. For example, an exemplary stepthat is described as “based on condition A” may be based on both acondition A and a condition B without departing from the scope of thepresent disclosure. In other words, as used herein, the phrase “basedon” shall be construed in the same manner as the phrase “based at leastin part on.”

The previous description of the disclosure is provided to enable aperson skilled in the art to make or use the disclosure. Variousmodifications to the disclosure will be readily apparent to thoseskilled in the art, and the generic principles defined herein may beapplied to other variations without departing from the scope of thedisclosure. Thus, the disclosure is not to be limited to the examplesand designs described herein but is to be accorded the broadest scopeconsistent with the principles and novel features disclosed herein.

1. (canceled)
 2. A method, comprising: communicating via an antenna;determining a plurality of peaked pointing directions from the antennato a target device based at least in part on measured signalcharacteristics associated with the communicating, wherein each of thepeaked pointing directions is associated with a respective spatialcondition; determining, after determining the plurality of peakedpointing directions, that a set of the respective spatial conditionssatisfies a spatial separation criteria; determining an offset between afirst reference frame of the antenna and a second reference frame thatis external to the antenna based at least in part on the peaked pointingdirections corresponding to the set of the respective spatialconditions; and communicating via the antenna based at least in part onthe determined offset.
 3. The method of claim 2, further comprising:determining, for each of the respective spatial conditions, a respectiveantenna pointing offset based at least in part on a difference betweenan estimated pointing direction from the antenna to the target deviceand the corresponding peaked pointing direction, wherein determining theoffset is based at least in part on the determined antenna pointingoffsets.
 4. The method of claim 3, further comprising: determining, foreach of the respective spatial conditions, a relative location of thetarget device from the antenna, wherein the estimated pointing directionis determined based at least in part on the relative location.
 5. Themethod of claim 2, wherein determining that the set of the respectivespatial conditions satisfies the spatial separation criteria comprises:determining that angular separation between adjacent pairs of the set ofrespective spatial conditions is less than or equal to a threshold. 6.The method of claim 2, wherein determining that the set of therespective spatial conditions satisfies the spatial separation criteriacomprises: determining that a quantity of angular ranges of antennaazimuth direction associated with the set of the respective spatialconditions satisfies a threshold.
 7. The method of claim 2, whereindetermining that the set of the respective spatial conditions satisfiesthe spatial separation criteria comprises: selecting a peaked pointingdirection from the plurality of peaked pointing directions fordetermining the offset based at least in part on a fitness metric of therespective spatial condition corresponding to the selected peak pointingdirection.
 8. The method of claim 2, wherein the second reference frameis associated with an inertial reference frame of a vehicle.
 9. Themethod of claim 2, wherein determining the plurality of peaked pointingdirections is based at least in part on a requested user data rate. 10.The method of claim 2, wherein the target device for determining one ofthe plurality of peaked pointing directions is different than the targetdevice for determining another of the plurality of peaked pointingdirections.
 11. The method of claim 2, wherein determining the offset isbased at least in part on satisfying an offset calibration qualitycriteria.
 12. The method of claim 2, wherein the measured signalcharacteristics are based at least in part on user data signals.
 13. Anapparatus, comprising: a processor; memory in electronic communicationwith the processor; and instructions stored in the memory and executableby the processor to cause the apparatus to: communicate via an antenna;determine a plurality of peaked pointing directions from the antenna toa target device based at least in part on measured signalcharacteristics associated with the communicating, wherein each of thepeaked pointing directions is associated with a respective spatialcondition; determine, after determining the plurality of peaked pointingdirections, that a set of the respective spatial conditions satisfies aspatial separation criteria; determine an offset between a firstreference frame of the antenna and a second reference frame that isexternal to the antenna based at least in part on the peaked pointingdirections corresponding to the set of the respective spatialconditions; and communicate via the antenna based at least in part onthe determined offset.
 14. The apparatus of claim 13, wherein theinstructions are executable by the processor to cause the apparatus todetermine the measured signal characteristics based at least in part onuser data signals communicated via the antenna.
 15. The apparatus ofclaim 13, wherein the instructions to cause the apparatus to determinethe plurality of peaked pointing directions are based at least in parton a requested data rate associated with the communication via theantenna.
 16. A system, comprising: an antenna; a modem coupled to theantenna and operable to process signals communicated via the antenna; apositioner for positioning a beam of the antenna based at least in parton positioning control information; and an alignment calibrationcontroller configured to: determine a plurality of peaked pointingdirections from the antenna to a target device based at least in part onmeasured signal characteristics associated with communication with thetarget device, wherein each of the peaked pointing directions isassociated with a respective spatial condition; determine, afterdetermining the plurality of peaked pointing directions, that a set ofthe respective spatial conditions satisfies a spatial separationcriteria; determine an offset between a first reference frame of theantenna and a second reference frame that is external to the antennabased at least in part on the peaked pointing directions correspondingto the set of the respective spatial conditions; and control thepositioner to position the antenna, for communications via the antenna,based at least in part on the determined offset.
 17. The system of claim16, wherein the positioner comprises a pointing mechanism configured tophysically position the beam of the antenna in response to thepositioning control information.
 18. The system of claim 16, wherein thepositioner comprises an electronic beamformer configured to steer thebeam of the antenna in response to the positioning control information.19. The system of claim 16, wherein the alignment calibration controlleris configured to determine the offset based at least in part on anoffset calibration quality criteria.
 20. The system of claim 16, whereinthe alignment calibration controller is configured to determine that theset of the respective spatial conditions satisfies the spatialseparation criteria based at least in part on determining that angularseparation between adjacent pairs of the spatial conditions is less thanor equal to a threshold.
 21. The system of claim 16, wherein thealignment calibration controller is configured to determine that the setof the respective spatial conditions satisfies the spatial separationcriteria based at least in part on determining that a number of angularranges of antenna azimuth direction associated with the spatialconditions satisfies a threshold.